AH 63-K-127/24 (ah63k127-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AH 63-K-127/24 (ah63k127-il) Reynolds number: 1,000,000 Max Cl/Cd: 152.31 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ah63k127-il-1000000.txt Download as CSV file: xf-ah63k127-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: AH 63-K-127/24
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.1730 0.08474 0.08194 -0.0976 0.7615 0.0094
-9.750 -0.1716 0.08074 0.07796 -0.0994 0.7607 0.0094
-9.500 -0.1692 0.07712 0.07436 -0.1012 0.7600 0.0094
-9.250 -0.1699 0.07270 0.06995 -0.1034 0.7593 0.0094
-9.000 -0.1723 0.06784 0.06512 -0.1063 0.7585 0.0094
-8.750 -0.1735 0.06334 0.06064 -0.1097 0.7576 0.0094
-8.500 -0.1843 0.05716 0.05446 -0.1147 0.7563 0.0094
-8.250 -0.1993 0.05291 0.05017 -0.1150 0.7553 0.0094
-8.000 -0.2095 0.04934 0.04653 -0.1142 0.7542 0.0094
-7.750 -0.2149 0.04537 0.04243 -0.1134 0.7530 0.0094
-7.500 -0.2457 0.03704 0.03376 -0.1110 0.7516 0.0098
-7.250 -0.2411 0.03381 0.03034 -0.1098 0.7504 0.0100
-7.000 -0.2296 0.03161 0.02798 -0.1089 0.7493 0.0102
-6.750 -0.2144 0.02973 0.02595 -0.1082 0.7483 0.0105
-6.500 -0.1973 0.02808 0.02415 -0.1075 0.7473 0.0110
-6.250 -0.1789 0.02624 0.02212 -0.1068 0.7464 0.0116
-6.000 -0.1590 0.02429 0.01994 -0.1059 0.7455 0.0125
-5.750 -0.1290 0.02526 0.02077 -0.1056 0.7446 0.0142
-5.000 -0.0700 0.01635 0.01096 -0.1025 0.7415 0.0125
-4.750 -0.0452 0.01455 0.00894 -0.1018 0.7403 0.0115
-4.500 -0.0193 0.01364 0.00794 -0.1015 0.7390 0.0116
-4.250 0.0053 0.01239 0.00656 -0.1008 0.7376 0.0106
-4.000 0.0309 0.01173 0.00582 -0.1004 0.7363 0.0103
-3.750 0.0567 0.01113 0.00515 -0.1002 0.7350 0.0105
-3.500 0.0833 0.01067 0.00462 -0.1000 0.7339 0.0106
-3.250 0.1103 0.01028 0.00418 -0.1000 0.7328 0.0113
-3.000 0.1378 0.00999 0.00384 -0.1000 0.7317 0.0129
-2.750 0.1655 0.00974 0.00354 -0.1001 0.7307 0.0152
-2.500 0.1926 0.00946 0.00326 -0.1001 0.7294 0.0287
-2.250 0.2179 0.00883 0.00305 -0.1000 0.7278 0.1420
-2.000 0.2431 0.00823 0.00292 -0.1001 0.7261 0.2845
-1.750 0.2661 0.00731 0.00275 -0.0999 0.7244 0.5233
-1.500 0.2898 0.00673 0.00272 -0.0993 0.7228 0.7021
-1.250 0.3167 0.00663 0.00273 -0.0991 0.7214 0.7564
-1.000 0.3452 0.00659 0.00268 -0.0992 0.7201 0.7720
-0.750 0.3737 0.00655 0.00263 -0.0994 0.7189 0.7846
-0.500 0.4021 0.00654 0.00260 -0.0995 0.7177 0.7971
-0.250 0.4303 0.00657 0.00261 -0.0996 0.7162 0.8079
0.000 0.4583 0.00656 0.00262 -0.0997 0.7141 0.8145
0.250 0.4866 0.00654 0.00260 -0.0999 0.7119 0.8204
0.500 0.5147 0.00651 0.00258 -0.1000 0.7098 0.8256
0.750 0.5434 0.00649 0.00254 -0.1002 0.7079 0.8312
1.000 0.5717 0.00644 0.00249 -0.1004 0.7061 0.8365
1.250 0.6000 0.00642 0.00247 -0.1005 0.7043 0.8419
1.500 0.6282 0.00642 0.00248 -0.1007 0.7019 0.8466
1.750 0.6561 0.00639 0.00248 -0.1008 0.6988 0.8500
2.000 0.6841 0.00634 0.00245 -0.1010 0.6958 0.8532
2.250 0.7125 0.00629 0.00242 -0.1012 0.6930 0.8562
2.500 0.7411 0.00627 0.00237 -0.1015 0.6903 0.8592
2.750 0.7690 0.00625 0.00240 -0.1017 0.6858 0.8620
3.000 0.7965 0.00618 0.00235 -0.1017 0.6804 0.8649
3.250 0.8238 0.00614 0.00233 -0.1017 0.6739 0.8683
3.500 0.8511 0.00612 0.00232 -0.1017 0.6662 0.8719
3.750 0.8784 0.00613 0.00234 -0.1017 0.6564 0.8749
4.000 0.9051 0.00614 0.00234 -0.1016 0.6465 0.8776
4.250 0.9311 0.00619 0.00240 -0.1014 0.6339 0.8803
4.500 0.9565 0.00628 0.00246 -0.1010 0.6170 0.8831
4.750 0.9808 0.00644 0.00256 -0.1005 0.5970 0.8863
5.000 1.0040 0.00668 0.00272 -0.0998 0.5714 0.8893
5.250 1.0266 0.00690 0.00290 -0.0990 0.5482 0.8924
5.500 1.0484 0.00718 0.00311 -0.0980 0.5236 0.8956
5.750 1.0704 0.00747 0.00334 -0.0971 0.4990 0.8990
6.000 1.0887 0.00795 0.00366 -0.0956 0.4594 0.9028
6.250 1.1023 0.00857 0.00407 -0.0932 0.4066 0.9073
6.500 1.1036 0.00973 0.00479 -0.0887 0.3133 0.9136
6.750 1.0976 0.01109 0.00565 -0.0829 0.2159 0.9214
7.000 1.0921 0.01214 0.00638 -0.0772 0.1502 0.9318
7.250 1.0947 0.01278 0.00691 -0.0729 0.1192 0.9481
7.500 1.1174 0.01336 0.00748 -0.0730 0.0991 1.0000
7.750 1.1291 0.01400 0.00805 -0.0708 0.0837 1.0000
8.000 1.1399 0.01472 0.00869 -0.0687 0.0689 1.0000
8.250 1.1503 0.01551 0.00943 -0.0667 0.0553 1.0000
8.500 1.1604 0.01640 0.01028 -0.0648 0.0430 1.0000
8.750 1.1710 0.01739 0.01123 -0.0632 0.0329 1.0000
9.000 1.1816 0.01845 0.01225 -0.0617 0.0239 1.0000
9.250 1.1915 0.01953 0.01329 -0.0601 0.0163 1.0000
9.500 1.1994 0.02073 0.01447 -0.0582 0.0103 1.0000
9.750 1.2068 0.02198 0.01573 -0.0563 0.0074 1.0000
10.000 1.2180 0.02300 0.01680 -0.0548 0.0065 1.0000
10.250 1.2288 0.02405 0.01790 -0.0533 0.0059 1.0000
10.500 1.2405 0.02505 0.01894 -0.0520 0.0055 1.0000
10.750 1.2483 0.02634 0.02030 -0.0503 0.0051 1.0000
11.000 1.2567 0.02760 0.02163 -0.0487 0.0048 1.0000
11.250 1.2585 0.02940 0.02355 -0.0465 0.0045 1.0000
11.500 1.2625 0.03107 0.02531 -0.0447 0.0044 1.0000
11.750 1.2749 0.03211 0.02640 -0.0437 0.0042 1.0000
12.000 1.2803 0.03374 0.02812 -0.0422 0.0042 1.0000
12.250 1.2901 0.03505 0.02950 -0.0411 0.0040 1.0000
12.500 1.2960 0.03670 0.03124 -0.0397 0.0039 1.0000
12.750 1.3040 0.03825 0.03286 -0.0386 0.0036 1.0000
13.000 1.3085 0.04016 0.03486 -0.0373 0.0035 1.0000
13.250 1.3138 0.04205 0.03684 -0.0362 0.0034 1.0000
13.500 1.3178 0.04413 0.03902 -0.0351 0.0033 1.0000
13.750 1.3231 0.04615 0.04116 -0.0342 0.0033 1.0000
14.000 1.3267 0.04841 0.04351 -0.0334 0.0032 1.0000
14.250 1.3284 0.05093 0.04616 -0.0325 0.0032 1.0000
14.500 1.3304 0.05350 0.04885 -0.0317 0.0032 1.0000
14.750 1.3313 0.05629 0.05177 -0.0311 0.0032 1.0000
15.000 1.3316 0.05923 0.05484 -0.0306 0.0031 1.0000
15.250 1.3310 0.06234 0.05810 -0.0302 0.0031 1.0000
15.500 1.3277 0.06595 0.06186 -0.0300 0.0031 1.0000
15.750 1.3238 0.06975 0.06582 -0.0300 0.0031 1.0000
16.000 1.3190 0.07374 0.06997 -0.0303 0.0031 1.0000
16.250 1.3179 0.07730 0.07362 -0.0310 0.0030 1.0000
16.500 1.3113 0.08183 0.07831 -0.0319 0.0030 1.0000
16.750 1.2958 0.08800 0.08472 -0.0332 0.0031 1.0000
17.000 1.2843 0.09368 0.09056 -0.0349 0.0031 1.0000
17.250 1.2823 0.09784 0.09480 -0.0366 0.0030 1.0000
17.500 1.2671 0.10458 0.10172 -0.0392 0.0030 1.0000
17.750 1.2548 0.11101 0.10830 -0.0420 0.0030 1.0000
18.000 1.2405 0.11806 0.11552 -0.0454 0.0030 1.0000
18.250 1.2195 0.12685 0.12451 -0.0499 0.0030 1.0000
18.500 1.1992 0.13592 0.13377 -0.0550 0.0031 1.0000
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