NACA 5-H-20 AIRFOIL (n5h20-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 5-H-20 AIRFOIL (n5h20-il) Reynolds number: 1,000,000 Max Cl/Cd: 75.41 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n5h20-il-1000000-n5.txt Download as CSV file: xf-n5h20-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 5-H-20 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.000 -0.8477 0.05650 0.05265 -0.0843 0.6753 0.0206
-16.750 -0.8822 0.04997 0.04589 -0.0864 0.6718 0.0206
-16.500 -0.8995 0.04621 0.04196 -0.0861 0.6674 0.0206
-16.250 -0.9150 0.04300 0.03858 -0.0848 0.6636 0.0206
-16.000 -0.9239 0.04054 0.03597 -0.0832 0.6595 0.0207
-15.750 -0.9275 0.03861 0.03390 -0.0813 0.6551 0.0207
-15.500 -0.9306 0.03678 0.03193 -0.0792 0.6508 0.0208
-15.250 -0.9337 0.03499 0.02998 -0.0769 0.6469 0.0208
-15.000 -0.9316 0.03358 0.02845 -0.0747 0.6436 0.0209
-14.750 -0.9271 0.03235 0.02711 -0.0726 0.6401 0.0209
-14.500 -0.9236 0.03105 0.02567 -0.0702 0.6362 0.0209
-14.250 -0.9232 0.02943 0.02389 -0.0675 0.6326 0.0211
-14.000 -0.9174 0.02822 0.02256 -0.0651 0.6290 0.0212
-13.750 -0.9083 0.02722 0.02148 -0.0631 0.6265 0.0213
-13.500 -0.8973 0.02635 0.02052 -0.0611 0.6236 0.0214
-13.250 -0.8851 0.02556 0.01965 -0.0593 0.6208 0.0215
-13.000 -0.8706 0.02498 0.01901 -0.0577 0.6181 0.0216
-12.750 -0.8564 0.02429 0.01824 -0.0560 0.6153 0.0217
-12.500 -0.8413 0.02362 0.01749 -0.0544 0.6126 0.0217
-12.250 -0.8248 0.02311 0.01693 -0.0530 0.6106 0.0219
-12.000 -0.8078 0.02249 0.01625 -0.0516 0.6089 0.0219
-11.750 -0.7900 0.02196 0.01566 -0.0503 0.6070 0.0221
-11.500 -0.7716 0.02144 0.01509 -0.0490 0.6051 0.0222
-11.250 -0.7525 0.02091 0.01449 -0.0479 0.6029 0.0223
-11.000 -0.7328 0.02054 0.01408 -0.0468 0.6007 0.0225
-10.750 -0.7125 0.02007 0.01355 -0.0458 0.5983 0.0226
-10.500 -0.6916 0.01959 0.01299 -0.0449 0.5959 0.0228
-10.250 -0.6702 0.01915 0.01248 -0.0440 0.5936 0.0230
-10.000 -0.6478 0.01865 0.01193 -0.0433 0.5924 0.0231
-9.750 -0.6251 0.01823 0.01147 -0.0426 0.5912 0.0232
-9.500 -0.6019 0.01778 0.01097 -0.0421 0.5898 0.0234
-9.250 -0.5783 0.01738 0.01052 -0.0416 0.5883 0.0236
-9.000 -0.5544 0.01699 0.01009 -0.0411 0.5868 0.0237
-8.750 -0.5301 0.01660 0.00966 -0.0406 0.5852 0.0238
-8.500 -0.5056 0.01625 0.00926 -0.0402 0.5836 0.0240
-8.250 -0.4810 0.01593 0.00889 -0.0398 0.5819 0.0241
-8.000 -0.4563 0.01561 0.00853 -0.0395 0.5803 0.0242
-7.750 -0.4314 0.01531 0.00819 -0.0391 0.5786 0.0244
-7.500 -0.4064 0.01504 0.00789 -0.0388 0.5768 0.0245
-7.250 -0.3813 0.01473 0.00754 -0.0385 0.5750 0.0246
-7.000 -0.3561 0.01437 0.00717 -0.0382 0.5740 0.0248
-6.750 -0.3308 0.01404 0.00684 -0.0379 0.5729 0.0251
-6.500 -0.3054 0.01377 0.00656 -0.0376 0.5717 0.0253
-6.250 -0.2800 0.01353 0.00632 -0.0374 0.5701 0.0256
-6.000 -0.2544 0.01332 0.00610 -0.0371 0.5683 0.0258
-5.750 -0.2288 0.01311 0.00589 -0.0369 0.5668 0.0261
-5.500 -0.2032 0.01292 0.00569 -0.0366 0.5649 0.0264
-5.250 -0.1776 0.01274 0.00550 -0.0364 0.5634 0.0268
-5.000 -0.1519 0.01258 0.00532 -0.0362 0.5620 0.0272
-4.750 -0.1263 0.01241 0.00514 -0.0359 0.5607 0.0275
-4.500 -0.1006 0.01226 0.00497 -0.0357 0.5591 0.0278
-4.250 -0.0750 0.01212 0.00482 -0.0354 0.5576 0.0281
-4.000 -0.0491 0.01197 0.00467 -0.0352 0.5567 0.0284
-3.750 -0.0233 0.01180 0.00451 -0.0350 0.5556 0.0287
-3.500 0.0024 0.01162 0.00435 -0.0348 0.5545 0.0292
-3.250 0.0282 0.01148 0.00422 -0.0346 0.5533 0.0298
-3.000 0.0539 0.01135 0.00411 -0.0344 0.5520 0.0304
-2.750 0.0796 0.01123 0.00400 -0.0341 0.5507 0.0310
-2.500 0.1052 0.01112 0.00389 -0.0339 0.5495 0.0317
-2.250 0.1308 0.01102 0.00380 -0.0337 0.5481 0.0323
-2.000 0.1562 0.01093 0.00370 -0.0334 0.5465 0.0331
-1.750 0.1812 0.01082 0.00361 -0.0331 0.5444 0.0345
-1.500 0.2061 0.01075 0.00354 -0.0327 0.5416 0.0363
-1.250 0.2311 0.01068 0.00347 -0.0324 0.5396 0.0380
-1.000 0.2561 0.01057 0.00341 -0.0321 0.5381 0.0409
-0.750 0.2809 0.01048 0.00335 -0.0317 0.5368 0.0450
-0.500 0.3054 0.01038 0.00330 -0.0313 0.5348 0.0516
-0.250 0.3296 0.01029 0.00325 -0.0308 0.5328 0.0602
0.000 0.3534 0.01021 0.00320 -0.0303 0.5313 0.0709
0.250 0.3753 0.01007 0.00315 -0.0294 0.5297 0.0972
0.500 0.3840 0.00963 0.00310 -0.0260 0.5283 0.2285
0.750 0.3851 0.00926 0.00304 -0.0210 0.5268 0.3319
1.000 0.3625 0.00877 0.00300 -0.0110 0.5256 0.4772
1.250 0.3442 0.00806 0.00276 -0.0019 0.5241 0.6198
1.500 0.3317 0.00751 0.00287 0.0065 0.5229 0.8144
1.750 0.3584 0.00765 0.00302 0.0066 0.5218 0.8293
2.000 0.3861 0.00778 0.00315 0.0065 0.5205 0.8351
2.250 0.4147 0.00803 0.00341 0.0062 0.5188 0.8426
2.500 0.4423 0.00827 0.00366 0.0061 0.5167 0.8488
2.750 0.4735 0.00859 0.00401 0.0054 0.5134 0.8529
3.000 0.5010 0.00877 0.00418 0.0052 0.5104 0.8554
3.250 0.5264 0.00887 0.00424 0.0053 0.5068 0.8563
3.500 0.5532 0.00888 0.00426 0.0051 0.5043 0.8566
3.750 0.5793 0.00892 0.00428 0.0050 0.5009 0.8569
4.000 0.6049 0.00896 0.00431 0.0051 0.4979 0.8571
4.250 0.6292 0.00902 0.00436 0.0053 0.4942 0.8574
4.500 0.6524 0.00911 0.00443 0.0057 0.4904 0.8577
4.750 0.6764 0.00918 0.00449 0.0060 0.4853 0.8579
5.000 0.6970 0.00931 0.00460 0.0068 0.4788 0.8582
5.250 0.7149 0.00948 0.00475 0.0081 0.4718 0.8586
5.500 0.7163 0.00984 0.00508 0.0122 0.4605 0.8593
5.750 0.7056 0.01066 0.00583 0.0180 0.4420 0.8601
6.000 0.6508 0.01296 0.00786 0.0301 0.3838 0.8613
6.250 0.6095 0.01511 0.00983 0.0395 0.3437 0.8628
6.500 0.6037 0.01628 0.01094 0.0436 0.3294 0.8634
6.750 0.6127 0.01697 0.01162 0.0456 0.3241 0.8639
7.000 0.6166 0.01790 0.01252 0.0482 0.3167 0.8644
7.250 0.6261 0.01867 0.01329 0.0499 0.3116 0.8649
7.500 0.6385 0.01936 0.01398 0.0513 0.3076 0.8654
7.750 0.6485 0.02016 0.01478 0.0529 0.3027 0.8658
8.000 0.6588 0.02100 0.01561 0.0543 0.2991 0.8662
8.250 0.6687 0.02187 0.01648 0.0558 0.2948 0.8666
8.500 0.6832 0.02255 0.01718 0.0567 0.2930 0.8669
8.750 0.6978 0.02322 0.01787 0.0576 0.2891 0.8673
9.000 0.7099 0.02404 0.01868 0.0587 0.2842 0.8676
9.250 0.7144 0.02530 0.01991 0.0605 0.2753 0.8681
9.500 0.7168 0.02671 0.02126 0.0624 0.2593 0.8685
9.750 0.7188 0.02817 0.02264 0.0642 0.2422 0.8690
10.000 0.7175 0.02986 0.02424 0.0663 0.2242 0.8695
10.250 0.7164 0.03156 0.02583 0.0682 0.2042 0.8699
10.500 0.7229 0.03284 0.02707 0.0694 0.1937 0.8703
10.750 0.7200 0.03471 0.02879 0.0714 0.1648 0.8708
11.000 0.7184 0.03652 0.03042 0.0731 0.1338 0.8712
11.250 0.7225 0.03806 0.03188 0.0743 0.1203 0.8716
11.500 0.7357 0.03902 0.03284 0.0747 0.1165 0.8719
11.750 0.7508 0.03988 0.03371 0.0750 0.1143 0.8722
12.000 0.7666 0.04071 0.03455 0.0751 0.1132 0.8725
12.250 0.7802 0.04169 0.03553 0.0754 0.1103 0.8728
12.500 0.7947 0.04264 0.03649 0.0756 0.1098 0.8731
12.750 0.8071 0.04373 0.03758 0.0759 0.1072 0.8734
13.000 0.8217 0.04467 0.03853 0.0760 0.1058 0.8737
13.250 0.8359 0.04565 0.03953 0.0762 0.1037 0.8739
13.500 0.8517 0.04653 0.04043 0.0762 0.1030 0.8742
13.750 0.8675 0.04741 0.04134 0.0761 0.1018 0.8745
14.000 0.8816 0.04844 0.04240 0.0762 0.1004 0.8747
14.250 0.8950 0.04954 0.04352 0.0762 0.0980 0.8750
14.500 0.9078 0.05067 0.04464 0.0763 0.0947 0.8752
14.750 0.9204 0.05181 0.04579 0.0763 0.0916 0.8755
15.000 0.9356 0.05277 0.04677 0.0762 0.0879 0.8757
15.250 0.9451 0.05419 0.04813 0.0763 0.0753 0.8759
15.500 0.9434 0.05659 0.05037 0.0769 0.0556 0.8763
15.750 0.9516 0.05822 0.05199 0.0769 0.0510 0.8769
16.000 0.9623 0.05964 0.05344 0.0768 0.0482 0.8775
16.250 0.9709 0.06129 0.05510 0.0767 0.0459 0.8780
16.500 0.9791 0.06299 0.05682 0.0766 0.0437 0.8785
16.750 0.9901 0.06444 0.05831 0.0764 0.0424 0.8790
17.000 1.0005 0.06595 0.05985 0.0761 0.0407 0.8794
17.250 1.0084 0.06774 0.06166 0.0759 0.0394 0.8798
17.500 1.0160 0.06955 0.06350 0.0757 0.0379 0.8802
17.750 1.0254 0.07119 0.06518 0.0754 0.0371 0.8806
18.000 1.0348 0.07286 0.06689 0.0750 0.0359 0.8811
18.250 1.0419 0.07479 0.06886 0.0747 0.0350 0.8815
18.500 1.0490 0.07671 0.07081 0.0743 0.0338 0.8819
18.750 1.0566 0.07861 0.07275 0.0739 0.0330 0.8824
19.000 1.0615 0.08083 0.07501 0.0734 0.0322 0.8828
19.250 1.0692 0.08273 0.07696 0.0729 0.0314 0.8832
|
Polar data table (+)
Polar graphs
<< Back to NACA 5-H-20 AIRFOIL (n5h20-il)