AH 93-K-132/15 (ah93k132-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: AH 93-K-132/15 (ah93k132-il) Reynolds number: 1,000,000 Max Cl/Cd: 134.6 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah93k132-il-1000000.txt Download as CSV file: xf-ah93k132-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4233 0.08597 0.08400 -0.0287 0.7853 0.0098
-8.750 -0.4269 0.07991 0.07796 -0.0340 0.7845 0.0098
-8.500 -0.4344 0.07292 0.07095 -0.0415 0.7836 0.0098
-8.250 -0.4442 0.06714 0.06509 -0.0443 0.7827 0.0099
-8.000 -0.4487 0.06066 0.05848 -0.0464 0.7819 0.0099
-7.750 -0.4774 0.04990 0.04743 -0.0466 0.7806 0.0102
-6.000 -0.4055 0.02240 0.01782 -0.0355 0.7724 0.0092
-5.750 -0.3844 0.02027 0.01538 -0.0343 0.7715 0.0092
-5.500 -0.3620 0.01823 0.01303 -0.0332 0.7707 0.0091
-5.250 -0.3381 0.01647 0.01102 -0.0323 0.7700 0.0089
-5.000 -0.3133 0.01524 0.00961 -0.0317 0.7693 0.0089
-4.750 -0.2880 0.01433 0.00858 -0.0312 0.7686 0.0090
-4.500 -0.2623 0.01364 0.00781 -0.0307 0.7679 0.0093
-4.250 -0.2359 0.01325 0.00732 -0.0305 0.7670 0.0098
-4.000 -0.2110 0.01238 0.00639 -0.0300 0.7656 0.0107
-3.750 -0.1835 0.01204 0.00606 -0.0302 0.7639 0.0116
-3.500 -0.1559 0.01173 0.00573 -0.0302 0.7622 0.0127
-3.250 -0.1281 0.01148 0.00545 -0.0303 0.7607 0.0136
-3.000 -0.1018 0.01099 0.00492 -0.0301 0.7594 0.0161
-2.750 -0.0739 0.01077 0.00469 -0.0301 0.7582 0.0184
-2.500 -0.0468 0.01040 0.00431 -0.0300 0.7571 0.0234
-2.250 -0.0195 0.01009 0.00401 -0.0299 0.7562 0.0333
-2.000 0.0073 0.00972 0.00376 -0.0298 0.7553 0.0653
-1.750 0.0332 0.00927 0.00353 -0.0296 0.7543 0.1337
-1.500 0.0584 0.00881 0.00338 -0.0294 0.7532 0.2295
-1.250 0.0832 0.00825 0.00328 -0.0293 0.7511 0.3616
-1.000 0.1031 0.00733 0.00314 -0.0282 0.7488 0.5872
-0.750 0.1173 0.00631 0.00303 -0.0253 0.7467 0.8411
-0.500 0.1505 0.00641 0.00335 -0.0257 0.7453 0.9207
-0.250 0.1756 0.00651 0.00341 -0.0249 0.7438 0.9393
0.000 0.2027 0.00668 0.00353 -0.0244 0.7424 0.9520
0.250 0.2390 0.00687 0.00367 -0.0259 0.7412 0.9606
0.500 0.2754 0.00695 0.00369 -0.0276 0.7398 0.9651
0.750 0.3167 0.00699 0.00373 -0.0307 0.7375 0.9669
1.000 0.3545 0.00701 0.00374 -0.0330 0.7349 0.9694
1.250 0.3854 0.00705 0.00376 -0.0337 0.7324 0.9748
1.500 0.4319 0.00697 0.00364 -0.0378 0.7301 0.9769
1.750 0.4726 0.00688 0.00352 -0.0406 0.7278 0.9801
2.000 0.5040 0.00687 0.00351 -0.0415 0.7243 0.9840
2.500 0.5740 0.00666 0.00331 -0.0451 0.7163 0.9869
2.750 0.6077 0.00655 0.00316 -0.0466 0.7127 0.9881
3.000 0.6415 0.00650 0.00315 -0.0482 0.7065 0.9893
3.250 0.6741 0.00642 0.00305 -0.0495 0.7010 0.9907
3.500 0.7064 0.00639 0.00304 -0.0508 0.6942 0.9923
3.750 0.7371 0.00636 0.00298 -0.0516 0.6860 0.9940
4.000 0.7702 0.00634 0.00295 -0.0531 0.6749 0.9949
4.250 0.8041 0.00633 0.00293 -0.0548 0.6629 0.9956
4.500 0.8375 0.00637 0.00293 -0.0564 0.6477 0.9964
4.750 0.8703 0.00651 0.00299 -0.0579 0.6240 0.9972
5.000 0.9028 0.00671 0.00310 -0.0595 0.6009 0.9980
5.250 0.9355 0.00695 0.00327 -0.0611 0.5746 0.9988
5.500 0.9683 0.00731 0.00350 -0.0629 0.5434 0.9996
5.750 0.9988 0.00769 0.00379 -0.0643 0.5132 1.0000
6.000 1.0256 0.00815 0.00412 -0.0650 0.4801 1.0000
6.250 1.0512 0.00870 0.00452 -0.0655 0.4432 1.0000
6.500 1.0753 0.00929 0.00496 -0.0658 0.4064 1.0000
6.750 1.0954 0.01023 0.00563 -0.0657 0.3509 1.0000
7.000 1.1117 0.01125 0.00638 -0.0651 0.2976 1.0000
7.250 1.1247 0.01221 0.00713 -0.0637 0.2553 1.0000
7.500 1.1326 0.01320 0.00794 -0.0614 0.2192 1.0000
7.750 1.1333 0.01414 0.00873 -0.0576 0.1888 1.0000
8.000 1.1205 0.01486 0.00936 -0.0508 0.1703 1.0000
8.250 1.1141 0.01560 0.01000 -0.0453 0.1497 1.0000
8.500 1.1126 0.01637 0.01066 -0.0408 0.1275 1.0000
8.750 1.1144 0.01711 0.01130 -0.0369 0.1086 1.0000
9.000 1.1180 0.01783 0.01196 -0.0335 0.0919 1.0000
9.250 1.1233 0.01856 0.01260 -0.0304 0.0774 1.0000
9.500 1.1296 0.01929 0.01328 -0.0275 0.0645 1.0000
9.750 1.1366 0.02004 0.01398 -0.0249 0.0532 1.0000
10.000 1.1454 0.02077 0.01466 -0.0226 0.0440 1.0000
10.250 1.1546 0.02153 0.01541 -0.0204 0.0360 1.0000
10.500 1.1636 0.02240 0.01624 -0.0184 0.0285 1.0000
10.750 1.1728 0.02335 0.01716 -0.0165 0.0219 1.0000
11.000 1.1850 0.02418 0.01799 -0.0151 0.0187 1.0000
11.250 1.1948 0.02521 0.01904 -0.0135 0.0157 1.0000
11.500 1.2079 0.02607 0.01994 -0.0124 0.0142 1.0000
11.750 1.2186 0.02711 0.02100 -0.0111 0.0126 1.0000
12.000 1.2278 0.02834 0.02229 -0.0097 0.0113 1.0000
12.250 1.2414 0.02929 0.02330 -0.0088 0.0106 1.0000
12.500 1.2538 0.03036 0.02441 -0.0079 0.0098 1.0000
12.750 1.2639 0.03161 0.02571 -0.0069 0.0091 1.0000
13.000 1.2681 0.03339 0.02756 -0.0053 0.0083 1.0000
13.250 1.2772 0.03482 0.02907 -0.0044 0.0079 1.0000
13.500 1.2885 0.03610 0.03041 -0.0036 0.0076 1.0000
13.750 1.2978 0.03756 0.03194 -0.0028 0.0072 1.0000
14.000 1.3068 0.03907 0.03352 -0.0021 0.0068 1.0000
14.250 1.3149 0.04072 0.03522 -0.0014 0.0065 1.0000
14.500 1.3206 0.04262 0.03720 -0.0006 0.0062 1.0000
14.750 1.3202 0.04514 0.03981 0.0005 0.0058 1.0000
15.000 1.3120 0.04851 0.04333 0.0017 0.0055 1.0000
15.250 1.3197 0.05041 0.04530 0.0021 0.0054 1.0000
15.500 1.3250 0.05258 0.04756 0.0024 0.0053 1.0000
15.750 1.3287 0.05494 0.05002 0.0027 0.0051 1.0000
16.000 1.3311 0.05751 0.05268 0.0030 0.0050 1.0000
16.250 1.3327 0.06022 0.05549 0.0031 0.0048 1.0000
16.500 1.3331 0.06316 0.05853 0.0031 0.0047 1.0000
16.750 1.3333 0.06618 0.06164 0.0030 0.0046 1.0000
17.000 1.3330 0.06930 0.06485 0.0027 0.0044 1.0000
17.250 1.3318 0.07261 0.06825 0.0023 0.0043 1.0000
17.500 1.3299 0.07610 0.07184 0.0018 0.0042 1.0000
17.750 1.3264 0.07987 0.07570 0.0011 0.0041 1.0000
18.000 1.3199 0.08411 0.08005 0.0002 0.0040 1.0000
18.250 1.3099 0.08892 0.08496 -0.0009 0.0039 1.0000
18.500 1.2962 0.09438 0.09055 -0.0022 0.0038 1.0000
18.750 1.2787 0.10053 0.09686 -0.0039 0.0037 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AH 93-K-132/15 (ah93k132-il)