AH 93-W-174 (ah93w174-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 93-W-174 (ah93w174-il) Reynolds number: 500,000 Max Cl/Cd: 113.59 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah93w174-il-500000.txt Download as CSV file: xf-ah93w174-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: AH 93-W-174
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.7736 0.08984 0.08678 -0.0577 1.0000 0.0274
-16.500 -0.8158 0.07853 0.07525 -0.0652 1.0000 0.0274
-16.250 -0.8408 0.07062 0.06717 -0.0705 1.0000 0.0275
-16.000 -0.8589 0.06415 0.06055 -0.0749 1.0000 0.0277
-15.750 -0.8742 0.05848 0.05473 -0.0787 1.0000 0.0279
-15.500 -0.8844 0.05377 0.04989 -0.0817 1.0000 0.0282
-15.250 -0.8935 0.04946 0.04544 -0.0844 1.0000 0.0284
-15.000 -0.8999 0.04574 0.04158 -0.0864 1.0000 0.0287
-14.750 -0.9042 0.04250 0.03820 -0.0880 1.0000 0.0290
-14.500 -0.9061 0.03976 0.03531 -0.0891 1.0000 0.0292
-14.250 -0.9097 0.03696 0.03240 -0.0895 1.0000 0.0295
-14.000 -0.9106 0.03458 0.02999 -0.0894 1.0000 0.0301
-13.750 -0.9068 0.03284 0.02822 -0.0891 1.0000 0.0305
-13.500 -0.8523 0.03055 0.02585 -0.0987 0.9288 0.0316
-13.250 -0.7704 0.02831 0.02305 -0.1139 0.8375 0.0333
-13.000 -0.7648 0.02734 0.02177 -0.1125 0.7920 0.0338
-12.750 -0.7584 0.02650 0.02069 -0.1110 0.7654 0.0342
-12.500 -0.7544 0.02503 0.01909 -0.1092 0.7461 0.0349
-12.250 -0.7471 0.02408 0.01803 -0.1075 0.7303 0.0356
-12.000 -0.7381 0.02338 0.01723 -0.1057 0.7172 0.0362
-11.750 -0.7287 0.02273 0.01650 -0.1037 0.7061 0.0370
-11.500 -0.7196 0.02219 0.01584 -0.1015 0.6972 0.0378
-11.250 -0.7059 0.02170 0.01523 -0.0998 0.6886 0.0389
-11.000 -0.6894 0.02124 0.01461 -0.0984 0.6814 0.0396
-10.750 -0.6759 0.02023 0.01357 -0.0970 0.6747 0.0407
-10.500 -0.6587 0.01965 0.01294 -0.0958 0.6683 0.0418
-10.250 -0.6392 0.01920 0.01242 -0.0948 0.6624 0.0429
-10.000 -0.6182 0.01878 0.01193 -0.0940 0.6567 0.0444
-9.750 -0.5963 0.01844 0.01146 -0.0933 0.6514 0.0457
-9.500 -0.5778 0.01773 0.01069 -0.0923 0.6468 0.0473
-9.250 -0.5560 0.01725 0.01021 -0.0916 0.6425 0.0489
-9.000 -0.5328 0.01689 0.00980 -0.0911 0.6380 0.0507
-8.750 -0.5090 0.01659 0.00940 -0.0906 0.6339 0.0525
-8.500 -0.4873 0.01607 0.00881 -0.0899 0.6298 0.0547
-8.250 -0.4634 0.01569 0.00844 -0.0894 0.6261 0.0572
-8.000 -0.4384 0.01539 0.00810 -0.0891 0.6222 0.0597
-7.750 -0.4140 0.01504 0.00768 -0.0886 0.6186 0.0623
-7.500 -0.3900 0.01465 0.00728 -0.0882 0.6152 0.0656
-7.250 -0.3641 0.01446 0.00702 -0.0880 0.6119 0.0690
-7.000 -0.3390 0.01409 0.00664 -0.0877 0.6090 0.0728
-6.750 -0.3133 0.01379 0.00636 -0.0875 0.6059 0.0770
-6.500 -0.2864 0.01363 0.00613 -0.0874 0.6027 0.0809
-6.250 -0.2613 0.01326 0.00578 -0.0871 0.5996 0.0869
-6.000 -0.2343 0.01313 0.00558 -0.0870 0.5964 0.0920
-5.750 -0.2082 0.01284 0.00532 -0.0869 0.5937 0.0989
-5.500 -0.1808 0.01268 0.00514 -0.0868 0.5911 0.1054
-5.250 -0.1543 0.01239 0.00491 -0.0867 0.5884 0.1146
-5.000 -0.1272 0.01218 0.00471 -0.0867 0.5857 0.1242
-4.750 -0.0997 0.01202 0.00454 -0.0867 0.5831 0.1348
-4.500 -0.0725 0.01184 0.00438 -0.0867 0.5804 0.1482
-4.250 -0.0451 0.01171 0.00426 -0.0867 0.5776 0.1636
-4.000 -0.0176 0.01150 0.00413 -0.0868 0.5754 0.1810
-3.750 0.0099 0.01130 0.00401 -0.0868 0.5729 0.2014
-3.500 0.0375 0.01110 0.00389 -0.0869 0.5705 0.2252
-3.250 0.0652 0.01092 0.00378 -0.0870 0.5681 0.2522
-3.000 0.0929 0.01072 0.00368 -0.0871 0.5658 0.2844
-2.750 0.1205 0.01053 0.00360 -0.0873 0.5634 0.3240
-2.500 0.1483 0.01039 0.00358 -0.0874 0.5608 0.3702
-2.250 0.1757 0.01014 0.00352 -0.0875 0.5587 0.4221
-2.000 0.2034 0.00994 0.00350 -0.0876 0.5565 0.4728
-1.750 0.2313 0.00980 0.00351 -0.0877 0.5542 0.5189
-1.500 0.2595 0.00972 0.00352 -0.0878 0.5520 0.5580
-1.250 0.2878 0.00967 0.00354 -0.0878 0.5497 0.5904
-1.000 0.3163 0.00967 0.00357 -0.0879 0.5475 0.6179
-0.750 0.3448 0.00974 0.00365 -0.0880 0.5451 0.6414
-0.500 0.3732 0.00979 0.00375 -0.0880 0.5430 0.6619
-0.250 0.4015 0.00981 0.00381 -0.0880 0.5411 0.6799
0.000 0.4299 0.00984 0.00388 -0.0881 0.5389 0.6953
0.250 0.4584 0.00989 0.00394 -0.0881 0.5366 0.7096
0.500 0.4870 0.00994 0.00399 -0.0882 0.5343 0.7235
0.750 0.5152 0.00999 0.00405 -0.0882 0.5321 0.7357
1.000 0.5436 0.01007 0.00413 -0.0882 0.5301 0.7471
1.250 0.5726 0.01027 0.00427 -0.0884 0.5279 0.7590
1.500 0.6000 0.01032 0.00440 -0.0883 0.5260 0.7691
1.750 0.6279 0.01038 0.00449 -0.0882 0.5239 0.7794
2.000 0.6555 0.01044 0.00460 -0.0881 0.5215 0.7899
2.250 0.6831 0.01050 0.00469 -0.0880 0.5192 0.7997
2.500 0.7112 0.01059 0.00478 -0.0880 0.5172 0.8097
2.750 0.7388 0.01066 0.00487 -0.0878 0.5152 0.8176
3.000 0.7669 0.01078 0.00497 -0.0879 0.5131 0.8260
3.250 0.7947 0.01095 0.00514 -0.0879 0.5107 0.8331
3.500 0.8214 0.01100 0.00526 -0.0877 0.5087 0.8408
3.750 0.8486 0.01107 0.00538 -0.0876 0.5065 0.8483
4.000 0.8752 0.01113 0.00549 -0.0873 0.5042 0.8555
4.250 0.9029 0.01121 0.00557 -0.0873 0.5018 0.8632
4.500 0.9293 0.01126 0.00565 -0.0870 0.4996 0.8698
4.750 0.9569 0.01136 0.00575 -0.0870 0.4975 0.8775
5.000 0.9839 0.01154 0.00593 -0.0869 0.4951 0.8842
5.250 1.0092 0.01160 0.00608 -0.0864 0.4929 0.8923
5.500 1.0342 0.01165 0.00621 -0.0859 0.4905 0.8999
5.750 1.0594 0.01171 0.00633 -0.0854 0.4879 0.9085
6.000 1.0841 0.01174 0.00640 -0.0848 0.4854 0.9169
6.250 1.1097 0.01179 0.00647 -0.0844 0.4830 0.9266
6.500 1.1335 0.01185 0.00655 -0.0836 0.4805 0.9368
6.750 1.1569 0.01193 0.00669 -0.0828 0.4777 0.9493
7.000 1.1826 0.01191 0.00677 -0.0824 0.4742 0.9657
7.250 1.2185 0.01192 0.00684 -0.0844 0.4702 0.9882
7.500 1.2487 0.01197 0.00689 -0.0851 0.4666 1.0000
7.750 1.2781 0.01214 0.00702 -0.0858 0.4626 1.0000
8.000 1.3042 0.01221 0.00720 -0.0858 0.4584 1.0000
8.250 1.3309 0.01226 0.00729 -0.0859 0.4536 1.0000
8.500 1.3577 0.01234 0.00734 -0.0859 0.4484 1.0000
8.750 1.3818 0.01243 0.00752 -0.0855 0.4423 1.0000
9.000 1.4059 0.01249 0.00761 -0.0850 0.4355 1.0000
9.250 1.4297 0.01265 0.00778 -0.0846 0.4293 1.0000
9.500 1.4528 0.01279 0.00799 -0.0840 0.4225 1.0000
9.750 1.4742 0.01298 0.00818 -0.0831 0.4147 1.0000
10.000 1.4944 0.01318 0.00842 -0.0820 0.4045 1.0000
10.250 1.5131 0.01343 0.00870 -0.0807 0.3940 1.0000
10.500 1.5289 0.01377 0.00904 -0.0789 0.3833 1.0000
10.750 1.5392 0.01418 0.00943 -0.0762 0.3708 1.0000
11.000 1.5475 0.01469 0.00993 -0.0732 0.3566 1.0000
11.250 1.5503 0.01542 0.01062 -0.0696 0.3402 1.0000
11.500 1.5499 0.01637 0.01153 -0.0659 0.3226 1.0000
11.750 1.5433 0.01775 0.01285 -0.0620 0.3029 1.0000
12.000 1.5309 0.01973 0.01477 -0.0582 0.2832 1.0000
12.250 1.5165 0.02225 0.01724 -0.0550 0.2650 1.0000
12.500 1.5012 0.02520 0.02013 -0.0525 0.2465 1.0000
12.750 1.4844 0.02850 0.02339 -0.0503 0.2285 1.0000
13.000 1.4685 0.03191 0.02676 -0.0484 0.2127 1.0000
13.250 1.4532 0.03540 0.03021 -0.0468 0.1979 1.0000
13.500 1.4379 0.03898 0.03375 -0.0454 0.1831 1.0000
13.750 1.4253 0.04247 0.03720 -0.0444 0.1700 1.0000
14.000 1.4134 0.04606 0.04076 -0.0435 0.1563 1.0000
14.250 1.4036 0.04959 0.04425 -0.0430 0.1435 1.0000
14.500 1.3951 0.05311 0.04773 -0.0425 0.1312 1.0000
14.750 1.3871 0.05671 0.05129 -0.0423 0.1194 1.0000
15.000 1.3805 0.06024 0.05478 -0.0422 0.1077 1.0000
15.250 1.3761 0.06360 0.05811 -0.0422 0.0971 1.0000
15.500 1.3716 0.06709 0.06159 -0.0424 0.0873 1.0000
15.750 1.3684 0.07047 0.06495 -0.0426 0.0784 1.0000
16.000 1.3648 0.07399 0.06846 -0.0429 0.0710 1.0000
16.250 1.3614 0.07755 0.07200 -0.0434 0.0637 1.0000
16.500 1.3601 0.08093 0.07537 -0.0439 0.0569 1.0000
16.750 1.3585 0.08438 0.07883 -0.0444 0.0513 1.0000
17.000 1.3552 0.08813 0.08258 -0.0451 0.0465 1.0000
17.250 1.3550 0.09152 0.08599 -0.0459 0.0423 1.0000
17.500 1.3532 0.09520 0.08970 -0.0467 0.0388 1.0000
17.750 1.3521 0.09879 0.09332 -0.0476 0.0355 1.0000
18.000 1.3502 0.10258 0.09714 -0.0486 0.0332 1.0000
18.250 1.3506 0.10606 0.10067 -0.0496 0.0308 1.0000
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