AH 93-K-131/15 (ah93k131-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 93-K-131/15 (ah93k131-il) Reynolds number: 1,000,000 Max Cl/Cd: 111.36 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah93k131-il-1000000-n5.txt Download as CSV file: xf-ah93k131-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 93-K-131/15
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
------ -------- --------- --------- -------- -------- --------
-12.750 -1.0157 0.03887 0.03589 -0.0379 0.7646 0.0056
-12.500 -1.0273 0.03424 0.03091 -0.0354 0.7633 0.0056
-12.250 -1.0247 0.03134 0.02775 -0.0334 0.7620 0.0057
-12.000 -1.0152 0.02921 0.02541 -0.0317 0.7607 0.0058
-11.750 -1.0017 0.02753 0.02355 -0.0304 0.7593 0.0059
-11.500 -0.9857 0.02612 0.02198 -0.0293 0.7580 0.0060
-11.250 -0.9678 0.02490 0.02060 -0.0283 0.7568 0.0062
-11.000 -0.9488 0.02379 0.01933 -0.0273 0.7556 0.0063
-10.750 -0.9287 0.02277 0.01818 -0.0265 0.7546 0.0064
-10.500 -0.9078 0.02181 0.01709 -0.0258 0.7535 0.0066
-10.250 -0.8863 0.02090 0.01605 -0.0251 0.7523 0.0067
-10.000 -0.8641 0.02005 0.01508 -0.0245 0.7509 0.0069
-9.750 -0.8414 0.01924 0.01415 -0.0239 0.7495 0.0071
-9.500 -0.8182 0.01850 0.01328 -0.0234 0.7481 0.0073
-9.250 -0.7945 0.01781 0.01246 -0.0229 0.7469 0.0074
-9.000 -0.7702 0.01718 0.01172 -0.0225 0.7457 0.0076
-8.750 -0.7454 0.01663 0.01106 -0.0221 0.7444 0.0077
-8.500 -0.7215 0.01590 0.01021 -0.0216 0.7431 0.0080
-8.250 -0.6966 0.01534 0.00958 -0.0213 0.7417 0.0084
-8.000 -0.6707 0.01491 0.00911 -0.0211 0.7406 0.0087
-7.750 -0.6445 0.01450 0.00864 -0.0210 0.7395 0.0090
-7.500 -0.6183 0.01409 0.00817 -0.0208 0.7381 0.0093
-7.250 -0.5920 0.01368 0.00771 -0.0207 0.7366 0.0097
-7.000 -0.5656 0.01329 0.00725 -0.0205 0.7351 0.0100
-6.750 -0.5390 0.01293 0.00682 -0.0204 0.7337 0.0104
-6.500 -0.5122 0.01260 0.00643 -0.0203 0.7324 0.0106
-6.250 -0.4860 0.01215 0.00592 -0.0201 0.7310 0.0113
-6.000 -0.4591 0.01184 0.00559 -0.0201 0.7296 0.0119
-5.750 -0.4318 0.01160 0.00532 -0.0201 0.7281 0.0125
-5.500 -0.4044 0.01137 0.00506 -0.0201 0.7267 0.0133
-5.250 -0.3769 0.01113 0.00480 -0.0201 0.7253 0.0139
-5.000 -0.3492 0.01091 0.00453 -0.0202 0.7236 0.0143
-4.750 -0.3223 0.01057 0.00418 -0.0201 0.7218 0.0154
-4.500 -0.2947 0.01035 0.00396 -0.0202 0.7201 0.0164
-4.250 -0.2671 0.01015 0.00374 -0.0202 0.7184 0.0173
-4.000 -0.2393 0.00997 0.00352 -0.0203 0.7167 0.0183
-3.750 -0.2114 0.00981 0.00334 -0.0204 0.7150 0.0190
-3.500 -0.1841 0.00957 0.00308 -0.0204 0.7133 0.0209
-3.250 -0.1561 0.00940 0.00293 -0.0206 0.7116 0.0223
-3.000 -0.1279 0.00925 0.00277 -0.0207 0.7096 0.0237
-2.750 -0.0997 0.00912 0.00263 -0.0209 0.7075 0.0248
-2.500 -0.0718 0.00893 0.00245 -0.0210 0.7053 0.0274
-2.250 -0.0438 0.00879 0.00230 -0.0212 0.7032 0.0298
-2.000 -0.0156 0.00867 0.00217 -0.0213 0.7011 0.0320
-1.750 0.0124 0.00855 0.00204 -0.0215 0.6990 0.0361
-1.500 0.0408 0.00842 0.00194 -0.0217 0.6969 0.0408
-1.250 0.0691 0.00831 0.00186 -0.0219 0.6945 0.0471
-1.000 0.0973 0.00818 0.00177 -0.0221 0.6918 0.0577
-0.750 0.1251 0.00802 0.00168 -0.0223 0.6890 0.0806
-0.500 0.1524 0.00783 0.00160 -0.0223 0.6863 0.1184
-0.250 0.1794 0.00759 0.00154 -0.0224 0.6836 0.1772
0.000 0.2054 0.00725 0.00149 -0.0223 0.6805 0.2711
0.250 0.2309 0.00691 0.00144 -0.0221 0.6771 0.3718
0.500 0.2476 0.00599 0.00135 -0.0202 0.6738 0.6317
0.750 0.2976 0.00534 0.00171 -0.0249 0.6710 0.9321
1.000 0.3122 0.00558 0.00195 -0.0216 0.6675 0.9600
1.250 0.3654 0.00593 0.00228 -0.0271 0.6637 0.9700
1.500 0.4045 0.00607 0.00238 -0.0296 0.6590 0.9742
1.750 0.4395 0.00611 0.00239 -0.0313 0.6540 0.9753
2.000 0.4716 0.00613 0.00239 -0.0325 0.6481 0.9762
2.250 0.5030 0.00617 0.00239 -0.0335 0.6420 0.9772
2.500 0.5341 0.00620 0.00241 -0.0344 0.6348 0.9782
2.750 0.5645 0.00626 0.00243 -0.0352 0.6276 0.9793
3.000 0.5945 0.00631 0.00247 -0.0359 0.6199 0.9804
3.250 0.6235 0.00639 0.00251 -0.0364 0.6114 0.9817
3.500 0.6505 0.00649 0.00259 -0.0365 0.6014 0.9833
3.750 0.6797 0.00658 0.00266 -0.0371 0.5908 0.9843
4.000 0.7115 0.00669 0.00273 -0.0383 0.5776 0.9847
4.250 0.7429 0.00684 0.00282 -0.0395 0.5607 0.9851
4.500 0.7742 0.00702 0.00294 -0.0407 0.5431 0.9856
4.750 0.8051 0.00723 0.00309 -0.0419 0.5243 0.9861
5.000 0.8350 0.00759 0.00332 -0.0430 0.4917 0.9866
5.250 0.8640 0.00804 0.00361 -0.0440 0.4555 0.9872
5.500 0.8932 0.00842 0.00389 -0.0451 0.4268 0.9879
5.750 0.9212 0.00893 0.00424 -0.0460 0.3909 0.9888
6.000 0.9470 0.00959 0.00468 -0.0467 0.3470 0.9897
6.250 0.9716 0.01024 0.00515 -0.0471 0.3076 0.9908
6.500 0.9953 0.01088 0.00563 -0.0474 0.2724 0.9921
6.750 1.0168 0.01161 0.00619 -0.0474 0.2366 0.9937
7.000 1.0401 0.01235 0.00678 -0.0478 0.2047 0.9946
7.250 1.0629 0.01338 0.00758 -0.0488 0.1613 0.9957
7.500 1.0838 0.01450 0.00849 -0.0495 0.1218 0.9972
8.000 1.1118 0.01624 0.01000 -0.0475 0.0778 1.0000
8.250 1.1113 0.01692 0.01064 -0.0431 0.0672 1.0000
8.500 1.1149 0.01761 0.01128 -0.0395 0.0571 1.0000
8.750 1.1216 0.01825 0.01190 -0.0366 0.0497 1.0000
9.000 1.1291 0.01890 0.01254 -0.0338 0.0433 1.0000
9.250 1.1362 0.01960 0.01321 -0.0311 0.0366 1.0000
9.500 1.1450 0.02026 0.01387 -0.0286 0.0319 1.0000
9.750 1.1530 0.02098 0.01457 -0.0261 0.0267 1.0000
10.000 1.1608 0.02175 0.01532 -0.0237 0.0223 1.0000
10.250 1.1700 0.02247 0.01604 -0.0215 0.0188 1.0000
10.750 1.1879 0.02403 0.01763 -0.0173 0.0137 1.0000
11.000 1.1969 0.02487 0.01847 -0.0153 0.0116 1.0000
11.250 1.2070 0.02568 0.01930 -0.0135 0.0104 1.0000
11.500 1.2164 0.02656 0.02021 -0.0117 0.0092 1.0000
11.750 1.2259 0.02748 0.02115 -0.0100 0.0082 1.0000
12.000 1.2362 0.02839 0.02210 -0.0085 0.0076 1.0000
12.250 1.2466 0.02937 0.02311 -0.0071 0.0070 1.0000
12.500 1.2562 0.03045 0.02424 -0.0057 0.0063 1.0000
12.750 1.2657 0.03162 0.02544 -0.0044 0.0058 1.0000
13.000 1.2768 0.03270 0.02657 -0.0034 0.0055 1.0000
13.250 1.2870 0.03389 0.02781 -0.0023 0.0052 1.0000
13.500 1.2971 0.03512 0.02909 -0.0013 0.0049 1.0000
13.750 1.3063 0.03646 0.03048 -0.0004 0.0046 1.0000
14.000 1.3152 0.03787 0.03194 0.0005 0.0044 1.0000
14.250 1.3229 0.03942 0.03355 0.0014 0.0042 1.0000
14.500 1.3292 0.04112 0.03532 0.0024 0.0040 1.0000
14.750 1.3363 0.04280 0.03707 0.0031 0.0039 1.0000
15.000 1.3441 0.04446 0.03879 0.0038 0.0038 1.0000
15.250 1.3506 0.04627 0.04068 0.0044 0.0037 1.0000
15.500 1.3568 0.04814 0.04262 0.0050 0.0036 1.0000
15.750 1.3620 0.05015 0.04470 0.0055 0.0035 1.0000
16.000 1.3665 0.05228 0.04691 0.0060 0.0035 1.0000
16.250 1.3707 0.05449 0.04920 0.0064 0.0034 1.0000
16.500 1.3739 0.05685 0.05164 0.0066 0.0033 1.0000
16.750 1.3762 0.05935 0.05422 0.0069 0.0032 1.0000
17.000 1.3780 0.06196 0.05692 0.0070 0.0031 1.0000
17.250 1.3790 0.06472 0.05977 0.0070 0.0031 1.0000
17.500 1.3791 0.06765 0.06279 0.0069 0.0030 1.0000
17.750 1.3781 0.07079 0.06602 0.0067 0.0030 1.0000
18.000 1.3760 0.07408 0.06940 0.0064 0.0029 1.0000
18.250 1.3729 0.07759 0.07301 0.0060 0.0029 1.0000
18.500 1.3688 0.08133 0.07684 0.0054 0.0028 1.0000
18.750 1.3634 0.08531 0.08092 0.0046 0.0028 1.0000
19.000 1.3569 0.08950 0.08522 0.0037 0.0027 1.0000
19.250 1.3488 0.09401 0.08983 0.0025 0.0027 1.0000
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Polar data table (+)
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