AH 93-K-132/15 (ah93k132-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 93-K-132/15 (ah93k132-il) Reynolds number: 1,000,000 Max Cl/Cd: 103.42 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah93k132-il-1000000-n5.txt Download as CSV file: xf-ah93k132-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 93-K-132/15
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4599 0.10893 0.10669 -0.0086 0.7706 0.0039
-10.250 -0.4635 0.10337 0.10114 -0.0112 0.7701 0.0040
-8.750 -0.6777 0.02732 0.02349 -0.0342 0.7653 0.0043
-8.500 -0.6669 0.02404 0.01978 -0.0323 0.7645 0.0043
-8.250 -0.6497 0.02192 0.01735 -0.0311 0.7636 0.0043
-8.000 -0.6289 0.02046 0.01565 -0.0303 0.7628 0.0044
-7.750 -0.6062 0.01934 0.01435 -0.0298 0.7620 0.0044
-7.500 -0.5823 0.01844 0.01330 -0.0293 0.7612 0.0045
-7.250 -0.5579 0.01761 0.01232 -0.0290 0.7603 0.0046
-7.000 -0.5355 0.01624 0.01073 -0.0283 0.7594 0.0047
-6.750 -0.5117 0.01520 0.00952 -0.0277 0.7586 0.0047
-6.500 -0.4869 0.01437 0.00855 -0.0273 0.7578 0.0048
-6.250 -0.4613 0.01372 0.00781 -0.0271 0.7570 0.0050
-6.000 -0.4352 0.01320 0.00722 -0.0269 0.7562 0.0051
-5.750 -0.4087 0.01275 0.00671 -0.0268 0.7555 0.0053
-5.500 -0.3819 0.01234 0.00624 -0.0267 0.7547 0.0055
-5.250 -0.3550 0.01197 0.00581 -0.0267 0.7539 0.0058
-5.000 -0.3280 0.01163 0.00542 -0.0267 0.7530 0.0061
-4.750 -0.3005 0.01130 0.00506 -0.0267 0.7520 0.0065
-4.500 -0.2728 0.01102 0.00476 -0.0269 0.7509 0.0068
-4.250 -0.2454 0.01069 0.00440 -0.0269 0.7497 0.0073
-4.000 -0.2177 0.01041 0.00410 -0.0270 0.7485 0.0079
-3.750 -0.1898 0.01018 0.00386 -0.0272 0.7472 0.0086
-3.500 -0.1619 0.00996 0.00363 -0.0274 0.7458 0.0094
-3.250 -0.1339 0.00973 0.00337 -0.0275 0.7444 0.0104
-3.000 -0.1060 0.00951 0.00315 -0.0276 0.7430 0.0122
-2.750 -0.0779 0.00932 0.00294 -0.0278 0.7417 0.0141
-2.500 -0.0499 0.00911 0.00274 -0.0279 0.7404 0.0174
-2.250 -0.0218 0.00893 0.00257 -0.0282 0.7390 0.0224
-2.000 0.0066 0.00876 0.00246 -0.0285 0.7371 0.0321
-1.750 0.0350 0.00860 0.00235 -0.0287 0.7351 0.0453
-1.500 0.0630 0.00839 0.00223 -0.0290 0.7331 0.0691
-1.250 0.0902 0.00808 0.00210 -0.0291 0.7311 0.1212
-1.000 0.1170 0.00772 0.00197 -0.0292 0.7291 0.1948
-0.750 0.1435 0.00736 0.00185 -0.0292 0.7273 0.2762
-0.500 0.1688 0.00689 0.00176 -0.0290 0.7251 0.3972
-0.250 0.1936 0.00642 0.00170 -0.0288 0.7221 0.5218
0.000 0.2070 0.00527 0.00163 -0.0260 0.7190 0.8250
0.250 0.2368 0.00529 0.00194 -0.0259 0.7163 0.9162
0.500 0.2662 0.00545 0.00206 -0.0260 0.7136 0.9328
0.750 0.2935 0.00554 0.00214 -0.0259 0.7101 0.9421
1.000 0.3219 0.00562 0.00220 -0.0261 0.7059 0.9481
1.250 0.3497 0.00568 0.00224 -0.0262 0.7017 0.9539
1.500 0.3785 0.00580 0.00233 -0.0264 0.6971 0.9605
1.750 0.4099 0.00591 0.00242 -0.0272 0.6905 0.9653
2.000 0.4455 0.00597 0.00244 -0.0290 0.6832 0.9676
2.250 0.4772 0.00602 0.00245 -0.0301 0.6742 0.9696
2.500 0.5053 0.00608 0.00247 -0.0303 0.6654 0.9720
2.750 0.5298 0.00616 0.00251 -0.0298 0.6562 0.9746
3.000 0.5619 0.00622 0.00253 -0.0310 0.6446 0.9751
3.250 0.5941 0.00631 0.00257 -0.0323 0.6313 0.9756
3.500 0.6263 0.00643 0.00263 -0.0336 0.6173 0.9761
3.750 0.6581 0.00657 0.00272 -0.0349 0.6024 0.9767
4.000 0.6893 0.00675 0.00284 -0.0361 0.5838 0.9773
4.250 0.7197 0.00699 0.00300 -0.0372 0.5615 0.9781
4.500 0.7498 0.00725 0.00319 -0.0383 0.5405 0.9790
4.750 0.7792 0.00754 0.00340 -0.0393 0.5176 0.9801
5.000 0.8066 0.00800 0.00371 -0.0400 0.4847 0.9816
5.250 0.8304 0.00848 0.00405 -0.0400 0.4506 0.9838
5.500 0.8549 0.00890 0.00437 -0.0401 0.4237 0.9853
5.750 0.8841 0.00946 0.00477 -0.0416 0.3858 0.9861
6.000 0.9121 0.01013 0.00526 -0.0430 0.3456 0.9871
6.250 0.9387 0.01084 0.00580 -0.0442 0.3088 0.9883
6.500 0.9633 0.01160 0.00639 -0.0451 0.2706 0.9899
6.750 0.9849 0.01241 0.00703 -0.0455 0.2351 0.9920
7.000 1.0034 0.01314 0.00763 -0.0451 0.2075 0.9943
7.250 1.0210 0.01407 0.00836 -0.0450 0.1677 0.9959
7.500 1.0358 0.01501 0.00909 -0.0442 0.1296 0.9977
7.750 1.0509 0.01582 0.00977 -0.0432 0.1041 0.9991
8.000 1.0647 0.01655 0.01040 -0.0419 0.0859 1.0000
8.250 1.0703 0.01713 0.01093 -0.0386 0.0742 1.0000
8.500 1.0765 0.01774 0.01150 -0.0354 0.0632 1.0000
8.750 1.0843 0.01832 0.01205 -0.0326 0.0542 1.0000
9.000 1.0931 0.01890 0.01261 -0.0300 0.0468 1.0000
9.250 1.1018 0.01953 0.01321 -0.0275 0.0396 1.0000
9.500 1.1117 0.02014 0.01381 -0.0252 0.0339 1.0000
9.750 1.1214 0.02080 0.01445 -0.0230 0.0281 1.0000
10.000 1.1316 0.02148 0.01511 -0.0209 0.0232 1.0000
10.250 1.1433 0.02215 0.01579 -0.0191 0.0199 1.0000
10.500 1.1545 0.02292 0.01656 -0.0174 0.0165 1.0000
10.750 1.1679 0.02363 0.01730 -0.0161 0.0143 1.0000
11.000 1.1801 0.02446 0.01813 -0.0147 0.0121 1.0000
11.250 1.1934 0.02527 0.01897 -0.0136 0.0108 1.0000
11.500 1.2069 0.02610 0.01982 -0.0125 0.0098 1.0000
11.750 1.2195 0.02701 0.02076 -0.0114 0.0088 1.0000
12.000 1.2320 0.02798 0.02177 -0.0104 0.0080 1.0000
12.250 1.2458 0.02891 0.02276 -0.0095 0.0074 1.0000
12.500 1.2591 0.02990 0.02379 -0.0087 0.0068 1.0000
12.750 1.2710 0.03101 0.02494 -0.0078 0.0063 1.0000
13.000 1.2821 0.03221 0.02618 -0.0069 0.0058 1.0000
13.250 1.2932 0.03343 0.02746 -0.0060 0.0055 1.0000
13.500 1.3050 0.03464 0.02872 -0.0053 0.0052 1.0000
13.750 1.3163 0.03590 0.03005 -0.0046 0.0050 1.0000
14.000 1.3265 0.03727 0.03148 -0.0039 0.0047 1.0000
14.250 1.3365 0.03869 0.03296 -0.0032 0.0044 1.0000
14.500 1.3452 0.04026 0.03459 -0.0025 0.0042 1.0000
14.750 1.3533 0.04192 0.03631 -0.0018 0.0040 1.0000
15.000 1.3591 0.04382 0.03829 -0.0011 0.0037 1.0000
15.250 1.3652 0.04572 0.04027 -0.0005 0.0036 1.0000
15.500 1.3724 0.04756 0.04218 0.0000 0.0035 1.0000
15.750 1.3784 0.04958 0.04428 0.0004 0.0034 1.0000
16.000 1.3839 0.05168 0.04647 0.0008 0.0033 1.0000
16.250 1.3886 0.05390 0.04878 0.0011 0.0031 1.0000
16.500 1.3920 0.05629 0.05125 0.0013 0.0030 1.0000
16.750 1.3949 0.05881 0.05387 0.0014 0.0029 1.0000
17.000 1.3970 0.06146 0.05660 0.0015 0.0028 1.0000
17.250 1.3981 0.06428 0.05952 0.0014 0.0028 1.0000
17.500 1.3984 0.06726 0.06258 0.0012 0.0027 1.0000
17.750 1.3975 0.07043 0.06584 0.0010 0.0026 1.0000
18.000 1.3954 0.07382 0.06933 0.0006 0.0025 1.0000
18.250 1.3918 0.07748 0.07309 0.0000 0.0025 1.0000
18.500 1.3864 0.08148 0.07720 -0.0007 0.0024 1.0000
18.750 1.3786 0.08587 0.08170 -0.0017 0.0023 1.0000
19.000 1.3693 0.09058 0.08652 -0.0028 0.0022 1.0000
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Polar data table (+)
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