AH 88-K-136/16 (ah88k136-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 88-K-136/16 (ah88k136-il) Reynolds number: 1,000,000 Max Cl/Cd: 95.66 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah88k136-il-1000000-n5.txt Download as CSV file: xf-ah88k136-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 88-K-136/16
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
------ -------- --------- --------- -------- -------- --------
-15.250 -0.8205 0.04626 0.04310 -0.1020 0.7789 0.0049
-15.000 -0.8578 0.04021 0.03684 -0.1030 0.7780 0.0049
-14.750 -0.8732 0.03717 0.03366 -0.1015 0.7772 0.0050
-14.500 -0.8868 0.03457 0.03092 -0.0990 0.7762 0.0051
-14.250 -0.8969 0.03241 0.02860 -0.0960 0.7753 0.0051
-14.000 -0.9060 0.03041 0.02643 -0.0925 0.7744 0.0051
-13.750 -0.9087 0.02884 0.02471 -0.0892 0.7737 0.0052
-13.500 -0.9009 0.02791 0.02370 -0.0869 0.7730 0.0053
-13.250 -0.9027 0.02642 0.02204 -0.0832 0.7723 0.0053
-13.000 -0.8956 0.02546 0.02098 -0.0805 0.7716 0.0054
-12.750 -0.8891 0.02446 0.01986 -0.0776 0.7709 0.0055
-12.500 -0.8792 0.02365 0.01896 -0.0751 0.7702 0.0056
-12.250 -0.8701 0.02277 0.01798 -0.0723 0.7694 0.0057
-12.000 -0.8590 0.02203 0.01714 -0.0698 0.7685 0.0057
-11.750 -0.8466 0.02137 0.01639 -0.0674 0.7675 0.0059
-11.500 -0.8329 0.02068 0.01560 -0.0653 0.7665 0.0061
-11.250 -0.8176 0.01994 0.01475 -0.0635 0.7656 0.0062
-11.000 -0.8008 0.01927 0.01398 -0.0618 0.7647 0.0062
-10.750 -0.7826 0.01865 0.01327 -0.0604 0.7638 0.0064
-10.500 -0.7639 0.01805 0.01257 -0.0591 0.7630 0.0066
-10.250 -0.7435 0.01756 0.01200 -0.0580 0.7623 0.0068
-10.000 -0.7232 0.01704 0.01138 -0.0568 0.7615 0.0069
-9.750 -0.7039 0.01637 0.01062 -0.0556 0.7607 0.0072
-9.500 -0.6829 0.01582 0.01000 -0.0545 0.7600 0.0074
-9.250 -0.6604 0.01542 0.00957 -0.0538 0.7592 0.0080
-9.000 -0.6383 0.01497 0.00905 -0.0529 0.7585 0.0081
-8.750 -0.6158 0.01454 0.00855 -0.0521 0.7577 0.0084
-8.500 -0.5928 0.01415 0.00808 -0.0514 0.7570 0.0087
-8.250 -0.5694 0.01381 0.00769 -0.0508 0.7563 0.0091
-8.000 -0.5457 0.01348 0.00732 -0.0502 0.7555 0.0093
-7.750 -0.5223 0.01309 0.00689 -0.0495 0.7546 0.0098
-7.500 -0.4985 0.01275 0.00653 -0.0489 0.7536 0.0105
-7.250 -0.4742 0.01246 0.00621 -0.0484 0.7525 0.0110
-7.000 -0.4497 0.01220 0.00592 -0.0479 0.7514 0.0116
-6.750 -0.4251 0.01193 0.00561 -0.0474 0.7504 0.0121
-6.500 -0.4006 0.01166 0.00531 -0.0469 0.7494 0.0127
-6.250 -0.3761 0.01137 0.00501 -0.0465 0.7485 0.0139
-6.000 -0.3511 0.01114 0.00477 -0.0460 0.7476 0.0149
-5.750 -0.3260 0.01092 0.00451 -0.0456 0.7466 0.0158
-5.500 -0.3010 0.01067 0.00426 -0.0452 0.7456 0.0172
-5.250 -0.2759 0.01045 0.00403 -0.0448 0.7448 0.0190
-5.000 -0.2505 0.01027 0.00382 -0.0445 0.7440 0.0204
-4.750 -0.2254 0.01005 0.00360 -0.0440 0.7431 0.0226
-4.500 -0.2000 0.00988 0.00342 -0.0437 0.7420 0.0249
-4.250 -0.1746 0.00972 0.00327 -0.0433 0.7409 0.0274
-4.000 -0.1492 0.00956 0.00314 -0.0430 0.7397 0.0314
-3.750 -0.1236 0.00941 0.00301 -0.0427 0.7384 0.0351
-3.500 -0.0980 0.00926 0.00287 -0.0424 0.7370 0.0399
-3.250 -0.0724 0.00911 0.00275 -0.0421 0.7357 0.0458
-3.000 -0.0465 0.00898 0.00263 -0.0418 0.7344 0.0514
-2.750 -0.0207 0.00882 0.00251 -0.0415 0.7330 0.0600
-2.500 0.0051 0.00868 0.00239 -0.0412 0.7318 0.0701
-2.250 0.0309 0.00853 0.00227 -0.0410 0.7304 0.0824
-2.000 0.0566 0.00837 0.00215 -0.0407 0.7289 0.0984
-1.750 0.0821 0.00822 0.00208 -0.0403 0.7270 0.1190
-1.500 0.1072 0.00807 0.00202 -0.0400 0.7247 0.1450
-1.250 0.1319 0.00787 0.00196 -0.0395 0.7222 0.1835
-1.000 0.1554 0.00760 0.00187 -0.0388 0.7197 0.2423
-0.750 0.1758 0.00717 0.00176 -0.0376 0.7172 0.3473
-0.500 0.1922 0.00663 0.00163 -0.0354 0.7146 0.4858
-0.250 0.1992 0.00597 0.00154 -0.0312 0.7118 0.6538
0.000 0.2043 0.00531 0.00168 -0.0260 0.7085 0.8603
0.250 0.2302 0.00541 0.00183 -0.0254 0.7055 0.8967
0.500 0.2541 0.00552 0.00192 -0.0245 0.7025 0.9115
0.750 0.2865 0.00568 0.00206 -0.0254 0.6996 0.9195
1.000 0.3069 0.00580 0.00219 -0.0237 0.6960 0.9278
1.250 0.3480 0.00603 0.00243 -0.0266 0.6921 0.9325
1.500 0.3810 0.00614 0.00252 -0.0277 0.6876 0.9354
1.750 0.4075 0.00615 0.00251 -0.0276 0.6837 0.9369
2.000 0.4327 0.00615 0.00251 -0.0272 0.6782 0.9385
2.250 0.4559 0.00614 0.00248 -0.0263 0.6722 0.9402
2.500 0.4774 0.00614 0.00246 -0.0252 0.6658 0.9421
2.750 0.4999 0.00614 0.00244 -0.0242 0.6580 0.9433
3.000 0.5274 0.00616 0.00245 -0.0243 0.6492 0.9440
3.250 0.5546 0.00621 0.00247 -0.0244 0.6376 0.9447
3.500 0.5809 0.00629 0.00251 -0.0243 0.6234 0.9456
3.750 0.6059 0.00640 0.00258 -0.0240 0.6075 0.9464
4.000 0.6287 0.00658 0.00268 -0.0232 0.5848 0.9474
4.250 0.6498 0.00680 0.00281 -0.0221 0.5616 0.9486
4.500 0.6706 0.00701 0.00297 -0.0210 0.5411 0.9500
4.750 0.6882 0.00730 0.00316 -0.0192 0.5168 0.9519
5.000 0.7046 0.00755 0.00335 -0.0172 0.4943 0.9539
5.250 0.7193 0.00780 0.00353 -0.0149 0.4748 0.9560
5.500 0.7315 0.00807 0.00374 -0.0121 0.4558 0.9579
5.750 0.7491 0.00844 0.00403 -0.0106 0.4282 0.9595
6.000 0.7605 0.00910 0.00450 -0.0083 0.3854 0.9620
6.250 0.7650 0.00980 0.00503 -0.0047 0.3466 0.9653
6.500 0.7638 0.01055 0.00564 -0.0001 0.3117 0.9696
6.750 0.7713 0.01155 0.00645 0.0019 0.2688 0.9726
7.000 0.7895 0.01255 0.00721 0.0017 0.2205 0.9740
7.250 0.8076 0.01362 0.00802 0.0014 0.1694 0.9751
7.500 0.8255 0.01451 0.00871 0.0016 0.1315 0.9764
7.750 0.8399 0.01549 0.00948 0.0023 0.0905 0.9779
8.000 0.8541 0.01643 0.01025 0.0031 0.0569 0.9795
8.250 0.8701 0.01724 0.01095 0.0038 0.0359 0.9809
8.500 0.8872 0.01795 0.01159 0.0044 0.0235 0.9824
8.750 0.9071 0.01849 0.01213 0.0047 0.0198 0.9836
9.000 0.9284 0.01914 0.01277 0.0046 0.0164 0.9842
9.250 0.9503 0.01972 0.01337 0.0043 0.0146 0.9849
9.500 0.9706 0.02039 0.01404 0.0043 0.0127 0.9856
9.750 0.9920 0.02098 0.01466 0.0042 0.0117 0.9864
10.000 1.0121 0.02163 0.01533 0.0041 0.0107 0.9873
10.250 1.0303 0.02241 0.01612 0.0044 0.0097 0.9884
10.500 1.0494 0.02310 0.01685 0.0045 0.0091 0.9895
10.750 1.0678 0.02385 0.01764 0.0047 0.0087 0.9908
11.000 1.0859 0.02459 0.01841 0.0049 0.0081 0.9922
11.250 1.1018 0.02545 0.01930 0.0053 0.0075 0.9936
12.000 1.1478 0.02824 0.02221 0.0069 0.0065 1.0000
12.250 1.1565 0.02915 0.02315 0.0087 0.0062 1.0000
12.500 1.1665 0.03011 0.02416 0.0101 0.0060 1.0000
12.750 1.1775 0.03109 0.02518 0.0113 0.0058 1.0000
13.000 1.1879 0.03217 0.02630 0.0124 0.0055 1.0000
13.250 1.1978 0.03334 0.02751 0.0134 0.0053 1.0000
13.500 1.2063 0.03466 0.02889 0.0146 0.0052 1.0000
13.750 1.2127 0.03619 0.03047 0.0157 0.0049 1.0000
14.000 1.2218 0.03754 0.03189 0.0166 0.0048 1.0000
14.250 1.2305 0.03897 0.03338 0.0174 0.0046 1.0000
14.500 1.2363 0.04069 0.03518 0.0183 0.0047 1.0000
14.750 1.2466 0.04202 0.03658 0.0189 0.0045 1.0000
15.000 1.2526 0.04379 0.03841 0.0196 0.0043 1.0000
15.250 1.2589 0.04559 0.04028 0.0202 0.0043 1.0000
15.500 1.2608 0.04787 0.04266 0.0210 0.0043 1.0000
15.750 1.2680 0.04965 0.04450 0.0213 0.0041 1.0000
16.000 1.2711 0.05189 0.04682 0.0218 0.0040 1.0000
16.250 1.2756 0.05404 0.04904 0.0220 0.0039 1.0000
16.500 1.2780 0.05649 0.05157 0.0222 0.0038 1.0000
16.750 1.2844 0.05852 0.05366 0.0222 0.0036 1.0000
17.000 1.2808 0.06176 0.05702 0.0223 0.0037 1.0000
17.250 1.2812 0.06460 0.05993 0.0222 0.0036 1.0000
17.500 1.2849 0.06710 0.06249 0.0219 0.0035 1.0000
17.750 1.2795 0.07082 0.06632 0.0215 0.0035 1.0000
18.000 1.2738 0.07466 0.07026 0.0209 0.0033 1.0000
18.250 1.2656 0.07892 0.07464 0.0201 0.0032 1.0000
18.500 1.2631 0.08251 0.07833 0.0193 0.0034 1.0000
18.750 1.2521 0.08739 0.08333 0.0181 0.0033 1.0000
19.000 1.2448 0.09184 0.08788 0.0168 0.0032 1.0000
19.250 1.2407 0.09587 0.09201 0.0155 0.0032 1.0000
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Polar data table (+)
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