I.S.A. 962 (isa962-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: I.S.A. 962 (isa962-il) Reynolds number: 50,000 Max Cl/Cd: 39.35 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-isa962-il-50000-n5.txt Download as CSV file: xf-isa962-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: I.S.A. 962
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3205 0.10577 0.09879 -0.0286 1.0000 0.1271
-8.750 -0.3389 0.10542 0.09862 -0.0291 1.0000 0.1278
-8.500 -0.3510 0.10432 0.09768 -0.0307 1.0000 0.1283
-8.250 -0.3372 0.09930 0.09269 -0.0264 1.0000 0.1296
-8.000 -0.3335 0.09643 0.08988 -0.0239 1.0000 0.1312
-7.750 -0.3353 0.09427 0.08780 -0.0221 1.0000 0.1329
-7.500 -0.3393 0.09235 0.08596 -0.0207 1.0000 0.1348
-7.250 -0.3441 0.09048 0.08416 -0.0197 1.0000 0.1369
-7.000 -0.3490 0.08863 0.08238 -0.0197 1.0000 0.1397
-6.750 -0.3556 0.08771 0.08140 -0.0271 1.0000 0.1441
-6.500 -0.3409 0.08343 0.07718 -0.0273 0.9964 0.1452
-6.250 -0.3191 0.07958 0.07334 -0.0275 0.9908 0.1484
-5.500 -0.2048 0.06106 0.05393 -0.0562 0.9666 0.0869
-5.250 -0.1716 0.05744 0.05017 -0.0602 0.9603 0.0829
-5.000 -0.1400 0.05369 0.04621 -0.0643 0.9522 0.0800
-4.750 -0.0978 0.04874 0.04079 -0.0709 0.9464 0.0764
-4.500 -0.0645 0.04551 0.03719 -0.0742 0.9384 0.0761
-4.250 -0.0271 0.04300 0.03443 -0.0777 0.9325 0.0774
-4.000 0.0063 0.04057 0.03165 -0.0802 0.9249 0.0778
-3.750 0.0450 0.03797 0.02858 -0.0832 0.9188 0.0773
-3.500 0.0833 0.03583 0.02601 -0.0858 0.9129 0.0772
-3.250 0.1169 0.03420 0.02403 -0.0873 0.9052 0.0776
-3.000 0.1586 0.03262 0.02211 -0.0900 0.9005 0.0787
-2.750 0.1883 0.03168 0.02092 -0.0906 0.8915 0.0814
-2.500 0.2276 0.03059 0.01944 -0.0925 0.8857 0.0849
-2.250 0.2578 0.02980 0.01851 -0.0928 0.8764 0.0873
-2.000 0.2959 0.02888 0.01749 -0.0943 0.8692 0.0904
-1.750 0.3266 0.02828 0.01672 -0.0943 0.8577 0.0941
-1.500 0.3620 0.02757 0.01587 -0.0949 0.8468 0.1010
-1.250 0.4003 0.02677 0.01494 -0.0958 0.8363 0.1127
-1.000 0.4293 0.02613 0.01433 -0.0954 0.8224 0.1260
-0.750 0.4578 0.02549 0.01388 -0.0951 0.8097 0.1574
-0.500 0.4884 0.02448 0.01358 -0.0955 0.7998 0.2911
-0.250 0.5205 0.02264 0.01322 -0.0954 0.7899 1.0000
0.000 0.5467 0.02280 0.01310 -0.0946 0.7777 1.0000
0.250 0.5756 0.02285 0.01293 -0.0942 0.7667 1.0000
0.500 0.6055 0.02285 0.01274 -0.0939 0.7559 1.0000
0.750 0.6309 0.02301 0.01277 -0.0931 0.7427 1.0000
1.000 0.6578 0.02312 0.01275 -0.0924 0.7299 1.0000
1.250 0.6863 0.02314 0.01265 -0.0919 0.7178 1.0000
1.500 0.7153 0.02313 0.01254 -0.0913 0.7054 1.0000
1.750 0.7409 0.02326 0.01259 -0.0904 0.6902 1.0000
2.000 0.7669 0.02333 0.01258 -0.0895 0.6740 1.0000
2.250 0.7932 0.02336 0.01253 -0.0884 0.6565 1.0000
2.500 0.8196 0.02335 0.01241 -0.0873 0.6377 1.0000
2.750 0.8423 0.02352 0.01252 -0.0859 0.6154 1.0000
3.000 0.8661 0.02362 0.01254 -0.0846 0.5925 1.0000
3.250 0.8905 0.02372 0.01251 -0.0833 0.5696 1.0000
3.500 0.9122 0.02400 0.01274 -0.0819 0.5446 1.0000
3.750 0.9356 0.02425 0.01288 -0.0807 0.5220 1.0000
4.000 0.9577 0.02463 0.01320 -0.0795 0.4994 1.0000
4.250 0.9797 0.02503 0.01353 -0.0783 0.4771 1.0000
4.500 1.0019 0.02546 0.01386 -0.0771 0.4561 1.0000
4.750 1.0228 0.02599 0.01431 -0.0758 0.4345 1.0000
5.000 1.0432 0.02656 0.01480 -0.0745 0.4132 1.0000
5.250 1.0634 0.02719 0.01532 -0.0732 0.3929 1.0000
5.500 1.0832 0.02789 0.01589 -0.0720 0.3737 1.0000
5.750 1.1022 0.02870 0.01663 -0.0707 0.3543 1.0000
6.000 1.1208 0.02957 0.01743 -0.0694 0.3354 1.0000
6.250 1.1392 0.03050 0.01832 -0.0681 0.3174 1.0000
6.500 1.1577 0.03146 0.01925 -0.0669 0.3009 1.0000
6.750 1.1759 0.03244 0.02020 -0.0657 0.2858 1.0000
7.000 1.1937 0.03342 0.02114 -0.0645 0.2722 1.0000
7.250 1.2108 0.03444 0.02228 -0.0632 0.2593 1.0000
7.500 1.2280 0.03549 0.02340 -0.0620 0.2481 1.0000
7.750 1.2451 0.03651 0.02442 -0.0608 0.2386 1.0000
8.000 1.2616 0.03757 0.02555 -0.0595 0.2296 1.0000
8.250 1.2784 0.03872 0.02681 -0.0584 0.2217 1.0000
8.500 1.2947 0.03981 0.02792 -0.0571 0.2145 1.0000
8.750 1.3102 0.04108 0.02930 -0.0559 0.2076 1.0000
9.000 1.3258 0.04230 0.03059 -0.0547 0.2014 1.0000
9.250 1.3432 0.04357 0.03191 -0.0537 0.1962 1.0000
9.500 1.3551 0.04512 0.03368 -0.0522 0.1907 1.0000
9.750 1.3709 0.04642 0.03501 -0.0511 0.1858 1.0000
10.000 1.3859 0.04795 0.03662 -0.0500 0.1813 1.0000
10.250 1.3925 0.04991 0.03889 -0.0482 0.1770 1.0000
10.500 1.4031 0.05174 0.04088 -0.0469 0.1733 1.0000
10.750 1.4211 0.05326 0.04244 -0.0462 0.1698 1.0000
11.000 1.4315 0.05532 0.04465 -0.0450 0.1666 1.0000
11.250 1.4238 0.05822 0.04791 -0.0426 0.1638 1.0000
11.500 1.4170 0.06123 0.05121 -0.0407 0.1611 1.0000
11.750 1.4125 0.06421 0.05443 -0.0392 0.1585 1.0000
12.000 1.4135 0.06689 0.05728 -0.0381 0.1559 1.0000
12.250 1.4225 0.06918 0.05966 -0.0373 0.1537 1.0000
12.500 1.4215 0.07244 0.06308 -0.0365 0.1519 1.0000
12.750 1.3806 0.07914 0.07014 -0.0361 0.1511 1.0000
13.000 1.3173 0.08979 0.08113 -0.0386 0.1505 1.0000
|
Polar data table (+)
Polar graphs
<< Back to I.S.A. 962 (isa962-il)