NACA 6-H-20 AIRFOIL (n6h20-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 6-H-20 AIRFOIL (n6h20-il) Reynolds number: 1,000,000 Max Cl/Cd: 83.05 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n6h20-il-1000000.txt Download as CSV file: xf-n6h20-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 6-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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.1064 0.10445 0.10144 -0.0481 0.6027 0.0246
-11.750 -0.1448 0.09925 0.09597 -0.0618 0.6046 0.0251
-11.500 -0.1449 0.08824 0.08524 -0.0562 0.6023 0.0266
-11.250 -0.1411 0.08521 0.08221 -0.0574 0.6017 0.0267
-11.000 -0.1389 0.08191 0.07892 -0.0587 0.6011 0.0268
-10.750 -0.1390 0.07823 0.07525 -0.0602 0.6006 0.0270
-10.500 -0.1383 0.07489 0.07192 -0.0616 0.5999 0.0272
-10.250 -0.1468 0.07011 0.06715 -0.0640 0.5994 0.0273
-10.000 -0.1677 0.06402 0.06106 -0.0675 0.5989 0.0275
-9.750 -0.4914 0.03878 0.03457 -0.0484 0.6013 0.0265
-9.500 -0.5065 0.03584 0.03133 -0.0422 0.6006 0.0265
-9.250 -0.5115 0.03340 0.02864 -0.0373 0.5998 0.0264
-9.000 -0.5080 0.03153 0.02654 -0.0336 0.5989 0.0264
-8.750 -0.5033 0.02943 0.02419 -0.0300 0.5981 0.0263
-8.500 -0.5001 0.02623 0.02062 -0.0263 0.5973 0.0265
-8.250 -0.4843 0.02415 0.01831 -0.0246 0.5965 0.0266
-8.000 -0.4627 0.02284 0.01686 -0.0238 0.5957 0.0269
-7.750 -0.4398 0.02227 0.01626 -0.0232 0.5948 0.0272
-7.500 -0.4155 0.02142 0.01530 -0.0227 0.5939 0.0274
-7.250 -0.3920 0.02122 0.01510 -0.0221 0.5927 0.0277
-7.000 -0.3669 0.02062 0.01441 -0.0219 0.5913 0.0280
-6.750 -0.3410 0.02005 0.01377 -0.0217 0.5909 0.0285
-6.500 -0.3105 0.01913 0.01274 -0.0224 0.5905 0.0287
-6.250 -0.2775 0.01828 0.01179 -0.0235 0.5900 0.0290
-6.000 -0.2409 0.01747 0.01089 -0.0254 0.5894 0.0292
-5.750 -0.1967 0.01662 0.00996 -0.0289 0.5888 0.0296
-5.500 -0.1561 0.01601 0.00928 -0.0316 0.5881 0.0299
-5.250 -0.1208 0.01562 0.00885 -0.0332 0.5873 0.0302
-5.000 -0.0859 0.01527 0.00846 -0.0347 0.5864 0.0304
-4.750 -0.0381 0.01460 0.00776 -0.0387 0.5857 0.0310
-4.500 -0.0010 0.01420 0.00740 -0.0407 0.5849 0.0318
-4.250 0.0315 0.01393 0.00713 -0.0418 0.5842 0.0321
-4.000 0.0624 0.01372 0.00693 -0.0425 0.5834 0.0326
-3.750 0.0932 0.01352 0.00673 -0.0432 0.5827 0.0331
-3.500 0.1229 0.01333 0.00654 -0.0437 0.5820 0.0336
-3.250 0.1520 0.01317 0.00638 -0.0441 0.5813 0.0341
-3.000 0.1807 0.01303 0.00623 -0.0444 0.5806 0.0345
-2.750 0.2091 0.01290 0.00609 -0.0447 0.5799 0.0351
-2.500 0.2371 0.01278 0.00596 -0.0449 0.5791 0.0356
-2.250 0.2650 0.01261 0.00580 -0.0451 0.5782 0.0366
-2.000 0.2918 0.01256 0.00576 -0.0451 0.5772 0.0378
-1.750 0.3177 0.01262 0.00583 -0.0450 0.5755 0.0391
-1.500 0.3444 0.01248 0.00571 -0.0450 0.5748 0.0402
-1.250 0.3705 0.01238 0.00563 -0.0449 0.5742 0.0418
-1.000 0.3963 0.01228 0.00557 -0.0447 0.5735 0.0440
-0.750 0.4218 0.01221 0.00552 -0.0445 0.5727 0.0466
-0.500 0.4463 0.01212 0.00550 -0.0441 0.5720 0.0561
-0.250 0.4677 0.01193 0.00551 -0.0431 0.5712 0.1039
0.000 0.4809 0.01158 0.00553 -0.0407 0.5702 0.2212
0.250 0.4847 0.01109 0.00538 -0.0364 0.5690 0.3341
0.500 0.4792 0.01044 0.00506 -0.0304 0.5678 0.4500
0.750 0.4551 0.00970 0.00457 -0.0205 0.5669 0.5356
1.000 0.4195 0.00933 0.00438 -0.0076 0.5660 0.6033
1.250 0.3813 0.00869 0.00408 0.0062 0.5651 0.7239
1.500 0.3907 0.00892 0.00461 0.0103 0.5642 0.8296
1.750 0.4155 0.00919 0.00484 0.0108 0.5634 0.8395
2.000 0.4536 0.00972 0.00541 0.0086 0.5624 0.8454
2.250 0.4881 0.01030 0.00598 0.0071 0.5610 0.8510
2.500 0.5176 0.01083 0.00651 0.0066 0.5598 0.8559
2.750 0.5796 0.01192 0.00769 -0.0002 0.5592 0.8608
3.000 0.8292 0.01534 0.01110 -0.0435 0.5577 0.8646
3.250 0.8480 0.01520 0.01098 -0.0422 0.5562 0.8653
3.500 0.8603 0.01507 0.01086 -0.0397 0.5551 0.8667
3.750 0.7117 0.01335 0.00915 -0.0054 0.5541 0.8708
4.000 0.8845 0.01489 0.01069 -0.0341 0.5521 0.8736
4.250 0.8446 0.01415 0.00996 -0.0212 0.5510 0.8739
4.500 1.0412 0.01628 0.01205 -0.0539 0.5484 0.8900
4.750 1.0697 0.01618 0.01193 -0.0545 0.5464 0.8903
5.000 1.0950 0.01615 0.01190 -0.0546 0.5445 0.8905
5.250 1.1209 0.01606 0.01186 -0.0548 0.5430 0.8907
5.500 1.1456 0.01599 0.01184 -0.0548 0.5415 0.8909
5.750 1.1691 0.01592 0.01180 -0.0546 0.5397 0.8911
6.000 1.1924 0.01584 0.01175 -0.0544 0.5377 0.8912
6.250 1.2155 0.01575 0.01168 -0.0541 0.5355 0.8914
6.500 1.2378 0.01569 0.01163 -0.0537 0.5337 0.8916
6.750 1.2594 0.01564 0.01158 -0.0531 0.5317 0.8917
7.000 1.2794 0.01562 0.01157 -0.0523 0.5293 0.8919
7.250 1.2964 0.01561 0.01162 -0.0509 0.5274 0.8920
7.500 1.0405 0.01254 0.00848 0.0033 0.5271 0.8781
7.750 1.0268 0.01264 0.00864 0.0099 0.5245 0.8785
8.000 1.0172 0.01307 0.00908 0.0154 0.5214 0.8788
8.250 1.0217 0.01341 0.00943 0.0184 0.5186 0.8790
8.500 1.0350 0.01359 0.00957 0.0201 0.5153 0.8791
8.750 1.0218 0.01458 0.01062 0.0254 0.5113 0.8794
9.000 1.0158 0.01546 0.01153 0.0296 0.5065 0.8797
9.250 1.0198 0.01604 0.01207 0.0323 0.5014 0.8800
9.500 1.0143 0.01706 0.01313 0.0362 0.4970 0.8803
9.750 1.0060 0.01822 0.01431 0.0404 0.4903 0.8806
10.000 1.0098 0.01894 0.01499 0.0429 0.4847 0.8809
10.250 0.9960 0.02053 0.01659 0.0474 0.4748 0.8812
10.500 0.9894 0.02189 0.01793 0.0509 0.4657 0.8815
10.750 0.9893 0.02300 0.01901 0.0536 0.4575 0.8817
11.000 0.9824 0.02452 0.02051 0.0568 0.4459 0.8820
11.250 0.9748 0.02613 0.02207 0.0601 0.4333 0.8822
11.500 0.9734 0.02747 0.02337 0.0625 0.4227 0.8826
11.750 0.9635 0.02933 0.02517 0.0657 0.4084 0.8830
12.000 0.9622 0.03079 0.02659 0.0679 0.3963 0.8831
12.250 0.9475 0.03308 0.02878 0.0713 0.3780 0.8833
12.500 0.9515 0.03436 0.03003 0.0727 0.3672 0.8834
12.750 0.9402 0.03662 0.03220 0.0755 0.3498 0.8836
13.000 0.9433 0.03807 0.03361 0.0768 0.3382 0.8837
13.250 0.9447 0.03965 0.03515 0.0782 0.3273 0.8838
13.500 0.9419 0.04158 0.03701 0.0798 0.3142 0.8840
13.750 0.9486 0.04292 0.03832 0.0806 0.3027 0.8841
14.000 0.9498 0.04466 0.04002 0.0817 0.2893 0.8842
14.250 0.9497 0.04655 0.04184 0.0828 0.2745 0.8843
14.750 0.9473 0.05062 0.04576 0.0849 0.2434 0.8846
15.000 0.9493 0.05248 0.04754 0.0857 0.2313 0.8847
15.250 0.9567 0.05394 0.04898 0.0860 0.2241 0.8848
15.500 0.9645 0.05543 0.05047 0.0862 0.2181 0.8850
15.750 0.9756 0.05669 0.05175 0.0862 0.2137 0.8851
16.000 0.9840 0.05815 0.05320 0.0862 0.2080 0.8852
16.250 0.9946 0.05946 0.05451 0.0862 0.2033 0.8854
16.500 1.0076 0.06059 0.05566 0.0859 0.1970 0.8855
16.750 1.0128 0.06239 0.05745 0.0860 0.1903 0.8856
17.000 1.0203 0.06401 0.05905 0.0860 0.1771 0.8858
17.250 1.0013 0.06800 0.06275 0.0871 0.1333 0.8859
17.500 0.9964 0.07077 0.06543 0.0876 0.1185 0.8860
17.750 0.9994 0.07289 0.06753 0.0875 0.1118 0.8861
18.000 1.0048 0.07487 0.06954 0.0873 0.1074 0.8862
18.250 1.0119 0.07667 0.07135 0.0870 0.1032 0.8864
18.500 1.0172 0.07867 0.07336 0.0867 0.0986 0.8865
18.750 1.0235 0.08063 0.07535 0.0863 0.0946 0.8866
19.000 1.0327 0.08229 0.07704 0.0858 0.0910 0.8867
19.250 1.0384 0.08429 0.07904 0.0853 0.0860 0.8868
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