AH 93-K-130/15 (ah93k130-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 93-K-130/15 (ah93k130-il) Reynolds number: 1,000,000 Max Cl/Cd: 108.88 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah93k130-il-1000000-n5.txt Download as CSV file: xf-ah93k130-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 93-K-130/15
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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.9751 0.03588 0.03277 -0.0409 0.7716 0.0061
-12.000 -0.9744 0.03268 0.02929 -0.0389 0.7709 0.0062
-11.750 -0.9665 0.03032 0.02669 -0.0373 0.7702 0.0063
-11.500 -0.9543 0.02845 0.02461 -0.0359 0.7696 0.0063
-11.250 -0.9399 0.02681 0.02275 -0.0346 0.7689 0.0064
-11.000 -0.9234 0.02541 0.02116 -0.0335 0.7682 0.0064
-10.750 -0.9105 0.02340 0.01888 -0.0318 0.7675 0.0066
-10.500 -0.8931 0.02198 0.01726 -0.0306 0.7669 0.0068
-10.250 -0.8728 0.02095 0.01609 -0.0298 0.7663 0.0070
-10.000 -0.8508 0.02012 0.01514 -0.0291 0.7657 0.0072
-9.750 -0.8280 0.01939 0.01431 -0.0286 0.7650 0.0073
-9.500 -0.8045 0.01874 0.01356 -0.0281 0.7643 0.0075
-9.250 -0.7807 0.01813 0.01284 -0.0277 0.7637 0.0077
-9.000 -0.7564 0.01752 0.01215 -0.0273 0.7632 0.0079
-8.750 -0.7318 0.01693 0.01147 -0.0270 0.7625 0.0081
-8.500 -0.7069 0.01637 0.01082 -0.0266 0.7618 0.0084
-8.250 -0.6817 0.01583 0.01020 -0.0264 0.7610 0.0086
-8.000 -0.6562 0.01533 0.00962 -0.0261 0.7601 0.0088
-7.750 -0.6304 0.01489 0.00909 -0.0259 0.7592 0.0090
-7.500 -0.6041 0.01451 0.00865 -0.0258 0.7583 0.0092
-7.250 -0.5792 0.01388 0.00794 -0.0254 0.7574 0.0097
-7.000 -0.5530 0.01347 0.00749 -0.0253 0.7565 0.0102
-6.750 -0.5264 0.01311 0.00710 -0.0252 0.7556 0.0106
-6.500 -0.4997 0.01279 0.00674 -0.0251 0.7548 0.0110
-6.250 -0.4729 0.01246 0.00636 -0.0250 0.7539 0.0114
-6.000 -0.4461 0.01215 0.00599 -0.0249 0.7530 0.0119
-5.750 -0.4191 0.01185 0.00565 -0.0249 0.7521 0.0124
-5.500 -0.3920 0.01158 0.00533 -0.0248 0.7512 0.0127
-5.250 -0.3655 0.01121 0.00493 -0.0247 0.7501 0.0137
-5.000 -0.3380 0.01099 0.00470 -0.0247 0.7491 0.0146
-4.750 -0.3102 0.01079 0.00451 -0.0249 0.7480 0.0156
-4.500 -0.2824 0.01060 0.00430 -0.0250 0.7467 0.0165
-4.250 -0.2546 0.01040 0.00409 -0.0251 0.7452 0.0171
-4.000 -0.2274 0.01012 0.00378 -0.0251 0.7437 0.0185
-3.750 -0.1997 0.00991 0.00357 -0.0252 0.7422 0.0198
-3.500 -0.1718 0.00972 0.00338 -0.0253 0.7408 0.0211
-3.250 -0.1439 0.00955 0.00320 -0.0254 0.7395 0.0224
-3.000 -0.1158 0.00940 0.00302 -0.0255 0.7383 0.0233
-2.750 -0.0883 0.00919 0.00280 -0.0255 0.7371 0.0258
-2.500 -0.0603 0.00904 0.00266 -0.0257 0.7359 0.0281
-2.250 -0.0320 0.00892 0.00255 -0.0259 0.7342 0.0302
-2.000 -0.0037 0.00878 0.00242 -0.0261 0.7322 0.0325
-1.750 0.0244 0.00863 0.00230 -0.0263 0.7301 0.0369
-1.500 0.0528 0.00851 0.00219 -0.0266 0.7281 0.0410
-1.250 0.0808 0.00835 0.00206 -0.0267 0.7261 0.0496
-1.000 0.1088 0.00820 0.00194 -0.0269 0.7243 0.0615
-0.750 0.1366 0.00803 0.00184 -0.0270 0.7224 0.0847
-0.500 0.1642 0.00783 0.00179 -0.0272 0.7196 0.1254
-0.250 0.1908 0.00754 0.00173 -0.0272 0.7162 0.1980
0.000 0.2169 0.00721 0.00165 -0.0271 0.7129 0.2828
0.250 0.2410 0.00672 0.00155 -0.0266 0.7099 0.4146
0.500 0.2515 0.00557 0.00145 -0.0234 0.7061 0.7318
0.750 0.3103 0.00535 0.00191 -0.0298 0.7022 0.9374
1.000 0.3302 0.00556 0.00210 -0.0278 0.6974 0.9606
1.250 0.3728 0.00588 0.00238 -0.0309 0.6922 0.9713
1.500 0.4170 0.00598 0.00245 -0.0346 0.6854 0.9738
1.750 0.4505 0.00600 0.00243 -0.0360 0.6790 0.9748
2.000 0.4825 0.00602 0.00242 -0.0371 0.6716 0.9757
2.250 0.5140 0.00605 0.00241 -0.0381 0.6637 0.9767
2.500 0.5448 0.00610 0.00242 -0.0390 0.6549 0.9777
2.750 0.5753 0.00616 0.00245 -0.0399 0.6450 0.9787
3.000 0.6051 0.00624 0.00249 -0.0406 0.6346 0.9798
3.250 0.6341 0.00635 0.00255 -0.0411 0.6233 0.9811
3.500 0.6613 0.00650 0.00265 -0.0413 0.6095 0.9827
3.750 0.6891 0.00667 0.00276 -0.0416 0.5924 0.9838
4.000 0.7211 0.00683 0.00285 -0.0430 0.5753 0.9843
4.250 0.7528 0.00699 0.00297 -0.0442 0.5598 0.9847
4.500 0.7838 0.00722 0.00312 -0.0454 0.5406 0.9852
4.750 0.8144 0.00748 0.00331 -0.0466 0.5172 0.9858
5.000 0.8440 0.00789 0.00358 -0.0477 0.4834 0.9864
5.250 0.8726 0.00833 0.00387 -0.0487 0.4493 0.9870
5.500 0.9004 0.00883 0.00421 -0.0496 0.4128 0.9878
5.750 0.9275 0.00940 0.00461 -0.0505 0.3744 0.9889
6.000 0.9513 0.01018 0.00514 -0.0510 0.3233 0.9902
6.250 0.9727 0.01100 0.00572 -0.0510 0.2735 0.9918
6.500 0.9908 0.01201 0.00645 -0.0506 0.2213 0.9938
6.750 1.0138 0.01296 0.00718 -0.0514 0.1779 0.9948
7.000 1.0365 0.01380 0.00786 -0.0520 0.1458 0.9959
7.250 1.0570 0.01469 0.00860 -0.0523 0.1143 0.9974
7.500 1.0713 0.01545 0.00925 -0.0511 0.0934 0.9990
7.750 1.0861 0.01612 0.00985 -0.0499 0.0781 1.0000
8.000 1.0894 0.01672 0.01041 -0.0461 0.0680 1.0000
8.250 1.0942 0.01736 0.01101 -0.0426 0.0577 1.0000
8.500 1.1007 0.01801 0.01161 -0.0396 0.0481 1.0000
8.750 1.1092 0.01860 0.01218 -0.0369 0.0408 1.0000
9.000 1.1178 0.01923 0.01279 -0.0342 0.0349 1.0000
9.250 1.1269 0.01985 0.01340 -0.0317 0.0302 1.0000
9.500 1.1370 0.02045 0.01400 -0.0294 0.0263 1.0000
9.750 1.1464 0.02111 0.01465 -0.0271 0.0232 1.0000
10.000 1.1560 0.02177 0.01532 -0.0248 0.0203 1.0000
10.250 1.1674 0.02237 0.01595 -0.0228 0.0189 1.0000
10.500 1.1777 0.02305 0.01664 -0.0207 0.0174 1.0000
10.750 1.1872 0.02380 0.01740 -0.0186 0.0157 1.0000
11.000 1.1981 0.02451 0.01814 -0.0168 0.0145 1.0000
11.250 1.2095 0.02522 0.01888 -0.0150 0.0137 1.0000
11.500 1.2200 0.02600 0.01970 -0.0133 0.0129 1.0000
11.750 1.2304 0.02683 0.02055 -0.0116 0.0121 1.0000
12.000 1.2403 0.02773 0.02148 -0.0099 0.0112 1.0000
12.250 1.2501 0.02870 0.02248 -0.0083 0.0104 1.0000
12.500 1.2622 0.02957 0.02340 -0.0070 0.0100 1.0000
12.750 1.2737 0.03053 0.02441 -0.0058 0.0095 1.0000
13.000 1.2846 0.03159 0.02550 -0.0047 0.0090 1.0000
13.250 1.2954 0.03269 0.02664 -0.0036 0.0084 1.0000
13.500 1.3049 0.03392 0.02791 -0.0024 0.0079 1.0000
13.750 1.3139 0.03524 0.02927 -0.0013 0.0073 1.0000
14.000 1.3247 0.03645 0.03055 -0.0004 0.0071 1.0000
14.250 1.3349 0.03775 0.03190 0.0004 0.0067 1.0000
14.500 1.3445 0.03911 0.03332 0.0012 0.0064 1.0000
14.750 1.3532 0.04059 0.03485 0.0020 0.0060 1.0000
15.000 1.3612 0.04215 0.03647 0.0028 0.0057 1.0000
15.250 1.3684 0.04384 0.03820 0.0035 0.0054 1.0000
15.500 1.3741 0.04572 0.04015 0.0043 0.0051 1.0000
15.750 1.3802 0.04758 0.04207 0.0049 0.0049 1.0000
16.000 1.3866 0.04946 0.04403 0.0054 0.0048 1.0000
16.250 1.3922 0.05146 0.04610 0.0059 0.0046 1.0000
16.500 1.3973 0.05354 0.04828 0.0063 0.0044 1.0000
16.750 1.4015 0.05578 0.05059 0.0066 0.0043 1.0000
17.000 1.4048 0.05814 0.05302 0.0068 0.0041 1.0000
17.250 1.4075 0.06060 0.05556 0.0070 0.0040 1.0000
17.500 1.4093 0.06321 0.05825 0.0071 0.0038 1.0000
17.750 1.4102 0.06601 0.06112 0.0071 0.0037 1.0000
18.000 1.4097 0.06902 0.06422 0.0070 0.0035 1.0000
18.250 1.4074 0.07228 0.06757 0.0068 0.0034 1.0000
18.500 1.4033 0.07585 0.07124 0.0064 0.0033 1.0000
18.750 1.3991 0.07954 0.07502 0.0059 0.0032 1.0000
19.000 1.3959 0.08316 0.07874 0.0052 0.0031 1.0000
19.250 1.3916 0.08698 0.08267 0.0044 0.0031 1.0000
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Polar data table (+)
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