NACA 5-H-20 AIRFOIL (n5h20-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 5-H-20 AIRFOIL (n5h20-il) Reynolds number: 500,000 Max Cl/Cd: 56.79 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n5h20-il-500000-n5.txt Download as CSV file: xf-n5h20-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.2840 0.10946 0.10546 -0.0535 0.6341 0.0232
-13.000 -0.6361 0.04752 0.04279 -0.0783 0.6441 0.0242
-12.750 -0.6897 0.04176 0.03657 -0.0724 0.6421 0.0243
-12.500 -0.7107 0.03869 0.03320 -0.0679 0.6396 0.0244
-12.250 -0.7257 0.03613 0.03031 -0.0634 0.6370 0.0245
-12.000 -0.7280 0.03434 0.02833 -0.0601 0.6343 0.0246
-11.750 -0.7251 0.03291 0.02675 -0.0572 0.6317 0.0247
-11.500 -0.7189 0.03172 0.02543 -0.0545 0.6294 0.0249
-11.250 -0.7106 0.03056 0.02415 -0.0521 0.6273 0.0249
-11.000 -0.6998 0.02969 0.02319 -0.0499 0.6252 0.0251
-10.750 -0.6880 0.02877 0.02216 -0.0478 0.6229 0.0252
-10.500 -0.6748 0.02788 0.02116 -0.0458 0.6207 0.0254
-10.250 -0.6603 0.02720 0.02038 -0.0440 0.6184 0.0256
-10.000 -0.6447 0.02643 0.01950 -0.0423 0.6161 0.0257
-9.750 -0.6281 0.02573 0.01868 -0.0407 0.6139 0.0260
-9.250 -0.5892 0.02413 0.01683 -0.0385 0.6100 0.0265
-9.000 -0.5664 0.02328 0.01587 -0.0379 0.6083 0.0267
-8.750 -0.5415 0.02243 0.01489 -0.0378 0.6065 0.0269
-8.500 -0.5156 0.02166 0.01401 -0.0378 0.6047 0.0272
-8.250 -0.4886 0.02095 0.01319 -0.0379 0.6029 0.0275
-8.000 -0.4607 0.02029 0.01243 -0.0382 0.6012 0.0277
-7.750 -0.4326 0.01970 0.01174 -0.0385 0.5995 0.0280
-7.500 -0.4049 0.01919 0.01114 -0.0387 0.5979 0.0282
-7.250 -0.3769 0.01871 0.01058 -0.0389 0.5963 0.0284
-7.000 -0.3488 0.01826 0.01005 -0.0392 0.5947 0.0286
-6.750 -0.3194 0.01772 0.00948 -0.0398 0.5931 0.0289
-6.500 -0.2918 0.01729 0.00906 -0.0400 0.5919 0.0292
-6.250 -0.2649 0.01694 0.00871 -0.0400 0.5906 0.0295
-6.000 -0.2384 0.01663 0.00840 -0.0400 0.5890 0.0299
-5.750 -0.2119 0.01634 0.00811 -0.0400 0.5875 0.0304
-5.500 -0.1855 0.01607 0.00782 -0.0399 0.5860 0.0308
-5.250 -0.1590 0.01578 0.00752 -0.0399 0.5845 0.0313
-5.000 -0.1328 0.01551 0.00722 -0.0398 0.5831 0.0318
-4.750 -0.1068 0.01524 0.00693 -0.0396 0.5816 0.0321
-4.500 -0.0810 0.01500 0.00666 -0.0394 0.5797 0.0325
-4.250 -0.0554 0.01480 0.00643 -0.0392 0.5782 0.0329
-4.000 -0.0302 0.01453 0.00615 -0.0389 0.5764 0.0335
-3.750 -0.0049 0.01434 0.00596 -0.0387 0.5749 0.0341
-3.500 0.0207 0.01415 0.00579 -0.0385 0.5739 0.0347
-3.250 0.0463 0.01398 0.00564 -0.0383 0.5728 0.0355
-3.000 0.0718 0.01383 0.00550 -0.0380 0.5717 0.0363
-2.750 0.0972 0.01368 0.00536 -0.0378 0.5705 0.0372
-2.500 0.1226 0.01353 0.00523 -0.0375 0.5693 0.0384
-2.250 0.1478 0.01340 0.00513 -0.0373 0.5681 0.0399
-2.000 0.1731 0.01328 0.00502 -0.0370 0.5667 0.0417
-1.750 0.1982 0.01317 0.00492 -0.0367 0.5654 0.0437
-1.500 0.2230 0.01305 0.00483 -0.0364 0.5637 0.0466
-1.250 0.2478 0.01296 0.00474 -0.0360 0.5621 0.0503
-1.000 0.2723 0.01286 0.00466 -0.0356 0.5605 0.0560
-0.750 0.2964 0.01277 0.00458 -0.0351 0.5590 0.0652
-0.500 0.3196 0.01266 0.00452 -0.0345 0.5575 0.0818
-0.250 0.3352 0.01221 0.00449 -0.0326 0.5565 0.1974
0.000 0.3311 0.01143 0.00437 -0.0270 0.5555 0.3837
0.250 0.3073 0.01082 0.00422 -0.0171 0.5544 0.5162
0.500 0.2755 0.01020 0.00401 -0.0052 0.5532 0.6197
1.250 0.3234 0.01101 0.00546 0.0029 0.5461 0.8432
1.500 0.3606 0.01174 0.00618 0.0013 0.5439 0.8520
1.750 0.3800 0.01207 0.00647 0.0031 0.5425 0.8610
2.000 0.4333 0.01291 0.00732 -0.0016 0.5410 0.8645
2.250 0.4787 0.01344 0.00784 -0.0050 0.5396 0.8667
2.500 0.5037 0.01348 0.00789 -0.0048 0.5384 0.8678
2.750 0.5224 0.01339 0.00780 -0.0034 0.5370 0.8687
3.000 0.5407 0.01329 0.00771 -0.0020 0.5355 0.8695
3.250 0.5594 0.01319 0.00762 -0.0007 0.5339 0.8702
3.500 0.5785 0.01311 0.00754 0.0006 0.5323 0.8710
3.750 0.5977 0.01303 0.00745 0.0018 0.5300 0.8716
4.000 0.6175 0.01296 0.00736 0.0029 0.5276 0.8723
4.250 0.6373 0.01290 0.00726 0.0040 0.5248 0.8729
4.500 0.6576 0.01287 0.00722 0.0049 0.5228 0.8734
4.750 0.6762 0.01287 0.00725 0.0061 0.5203 0.8740
5.000 0.6949 0.01288 0.00728 0.0073 0.5179 0.8746
5.250 0.7118 0.01290 0.00732 0.0087 0.5150 0.8752
5.500 0.7271 0.01295 0.00737 0.0105 0.5120 0.8759
5.750 0.7377 0.01299 0.00741 0.0131 0.5090 0.8765
6.000 0.7440 0.01316 0.00759 0.0163 0.5056 0.8771
6.250 0.7526 0.01349 0.00796 0.0189 0.5016 0.8777
6.500 0.7638 0.01381 0.00832 0.0209 0.4977 0.8782
6.750 0.7757 0.01414 0.00865 0.0229 0.4939 0.8787
7.000 0.7870 0.01450 0.00901 0.0249 0.4895 0.8793
7.250 0.7966 0.01495 0.00950 0.0271 0.4833 0.8798
7.500 0.8037 0.01546 0.01000 0.0296 0.4762 0.8804
7.750 0.8094 0.01608 0.01063 0.0322 0.4661 0.8811
8.000 0.8131 0.01677 0.01131 0.0350 0.4546 0.8818
8.250 0.7925 0.01834 0.01273 0.0409 0.4201 0.8829
8.500 0.7293 0.02201 0.01609 0.0513 0.3656 0.8850
8.750 0.7075 0.02436 0.01833 0.0562 0.3457 0.8861
9.000 0.7013 0.02605 0.01996 0.0592 0.3342 0.8868
9.250 0.7062 0.02722 0.02112 0.0610 0.3274 0.8873
9.500 0.7141 0.02825 0.02213 0.0625 0.3220 0.8877
9.750 0.7212 0.02936 0.02323 0.0639 0.3173 0.8881
10.000 0.7308 0.03032 0.02419 0.0651 0.3129 0.8885
10.250 0.7429 0.03119 0.02507 0.0660 0.3072 0.8889
10.500 0.7479 0.03248 0.02633 0.0674 0.2988 0.8893
10.750 0.7577 0.03351 0.02734 0.0684 0.2937 0.8897
11.000 0.7716 0.03432 0.02818 0.0690 0.2870 0.8900
11.250 0.7838 0.03526 0.02913 0.0696 0.2822 0.8903
11.500 0.7910 0.03654 0.03038 0.0707 0.2713 0.8906
11.750 0.7984 0.03782 0.03162 0.0716 0.2590 0.8909
12.000 0.8076 0.03902 0.03280 0.0724 0.2477 0.8912
12.250 0.8074 0.04091 0.03458 0.0737 0.2289 0.8917
12.500 0.8147 0.04231 0.03593 0.0744 0.2167 0.8922
12.750 0.8183 0.04398 0.03753 0.0753 0.2013 0.8926
13.000 0.8274 0.04528 0.03881 0.0758 0.1906 0.8931
13.250 0.8232 0.04757 0.04088 0.0771 0.1516 0.8936
13.500 0.8258 0.04941 0.04261 0.0778 0.1341 0.8940
13.750 0.8330 0.05095 0.04411 0.0783 0.1255 0.8944
14.000 0.8434 0.05226 0.04541 0.0785 0.1208 0.8949
14.250 0.8538 0.05359 0.04675 0.0786 0.1169 0.8953
14.500 0.8666 0.05476 0.04796 0.0786 0.1149 0.8957
14.750 0.8781 0.05606 0.04930 0.0787 0.1122 0.8962
15.000 0.8895 0.05737 0.05064 0.0787 0.1098 0.8967
15.250 0.8991 0.05883 0.05212 0.0787 0.1065 0.8973
15.500 0.9088 0.06030 0.05361 0.0787 0.1037 0.8979
15.750 0.9220 0.06150 0.05487 0.0786 0.1014 0.8985
16.000 0.9338 0.06284 0.05626 0.0784 0.0981 0.8990
16.250 0.9428 0.06445 0.05788 0.0783 0.0929 0.8995
16.500 0.9549 0.06579 0.05927 0.0780 0.0876 0.9000
16.750 0.9569 0.06810 0.06144 0.0780 0.0658 0.9005
17.250 0.9634 0.07258 0.06587 0.0778 0.0535 0.9015
17.500 0.9667 0.07490 0.06821 0.0776 0.0505 0.9019
17.750 0.9730 0.07696 0.07032 0.0772 0.0484 0.9024
18.000 0.9793 0.07903 0.07244 0.0768 0.0467 0.9029
18.250 0.9833 0.08139 0.07485 0.0764 0.0452 0.9034
18.500 0.9861 0.08388 0.07738 0.0759 0.0437 0.9039
18.750 0.9913 0.08615 0.07971 0.0754 0.0423 0.9044
19.000 0.9964 0.08847 0.08210 0.0747 0.0416 0.9049
19.250 1.0012 0.09084 0.08452 0.0741 0.0404 0.9054
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