FX 84-W-150 (fx84w150-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 84-W-150 (fx84w150-il) Reynolds number: 100,000 Max Cl/Cd: 47.44 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx84w150-il-100000-n5.txt Download as CSV file: xf-fx84w150-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 84-W-150
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.2346 0.09459 0.08947 -0.0841 0.9522 0.0410
-10.750 -0.2341 0.08826 0.08313 -0.0894 0.9456 0.0413
-10.500 -0.2386 0.08161 0.07648 -0.0945 0.9371 0.0414
-10.250 -0.2519 0.07268 0.06755 -0.1016 0.9290 0.0413
-10.000 -0.2977 0.05851 0.05325 -0.1139 0.9148 0.0407
-9.750 -0.3339 0.05238 0.04688 -0.1170 0.9001 0.0403
-9.500 -0.3622 0.04853 0.04274 -0.1157 0.8876 0.0403
-9.250 -0.3782 0.04464 0.03845 -0.1144 0.8787 0.0407
-9.000 -0.3866 0.04123 0.03457 -0.1126 0.8697 0.0412
-8.750 -0.3886 0.03787 0.03059 -0.1108 0.8629 0.0423
-8.500 -0.3766 0.03647 0.02905 -0.1096 0.8558 0.0436
-8.250 -0.3590 0.03538 0.02782 -0.1088 0.8507 0.0452
-8.000 -0.3445 0.03390 0.02609 -0.1077 0.8447 0.0469
-7.750 -0.3298 0.03208 0.02387 -0.1064 0.8384 0.0487
-7.500 -0.3108 0.03039 0.02178 -0.1055 0.8340 0.0507
-7.250 -0.2906 0.02968 0.02105 -0.1048 0.8285 0.0529
-7.000 -0.2703 0.02876 0.01996 -0.1040 0.8226 0.0554
-6.750 -0.2474 0.02754 0.01842 -0.1033 0.8183 0.0582
-6.500 -0.2245 0.02662 0.01742 -0.1028 0.8141 0.0610
-6.250 -0.2037 0.02606 0.01681 -0.1020 0.8078 0.0642
-6.000 -0.1794 0.02522 0.01577 -0.1014 0.8033 0.0680
-5.750 -0.1543 0.02441 0.01489 -0.1010 0.7999 0.0719
-5.500 -0.1333 0.02397 0.01443 -0.1002 0.7937 0.0764
-5.250 -0.1095 0.02337 0.01369 -0.0995 0.7888 0.0814
-5.000 -0.0846 0.02277 0.01311 -0.0992 0.7851 0.0873
-4.750 -0.0607 0.02231 0.01253 -0.0985 0.7806 0.0941
-4.500 -0.0395 0.02191 0.01219 -0.0977 0.7745 0.1015
-4.250 -0.0147 0.02143 0.01168 -0.0972 0.7704 0.1112
-4.000 0.0117 0.02096 0.01116 -0.0969 0.7673 0.1238
-3.750 0.0322 0.02075 0.01099 -0.0960 0.7608 0.1375
-3.500 0.0560 0.02038 0.01068 -0.0954 0.7559 0.1560
-3.250 0.0820 0.01993 0.01029 -0.0951 0.7524 0.1817
-3.000 0.1051 0.01961 0.01010 -0.0945 0.7476 0.2157
-2.750 0.1265 0.01930 0.00999 -0.0937 0.7417 0.2632
-2.500 0.1506 0.01874 0.00973 -0.0932 0.7377 0.3427
-2.250 0.1742 0.01804 0.00953 -0.0924 0.7347 0.4706
-2.000 0.1895 0.01793 0.00991 -0.0900 0.7278 0.5898
-1.750 0.2113 0.01785 0.01003 -0.0882 0.7233 0.6767
-1.500 0.2357 0.01781 0.01001 -0.0867 0.7200 0.7335
-1.250 0.2556 0.01798 0.01020 -0.0847 0.7147 0.7731
-1.000 0.2755 0.01815 0.01035 -0.0828 0.7092 0.8054
-0.750 0.2997 0.01816 0.01031 -0.0814 0.7055 0.8347
-0.500 0.3263 0.01811 0.01017 -0.0803 0.7026 0.8611
-0.250 0.3435 0.01843 0.01050 -0.0782 0.6955 0.8849
0.000 0.3708 0.01848 0.01049 -0.0775 0.6912 0.9125
0.250 0.4145 0.01844 0.01035 -0.0798 0.6883 0.9379
0.500 0.4569 0.01850 0.01033 -0.0826 0.6841 0.9547
0.750 0.4953 0.01867 0.01044 -0.0852 0.6782 0.9656
1.000 0.5373 0.01862 0.01031 -0.0882 0.6742 0.9740
1.250 0.5803 0.01849 0.01007 -0.0913 0.6712 0.9815
1.500 0.6167 0.01873 0.01031 -0.0938 0.6647 0.9911
1.750 0.6538 0.01877 0.01030 -0.0962 0.6597 1.0000
2.000 0.6736 0.01873 0.01018 -0.0949 0.6559 1.0000
2.250 0.6803 0.01907 0.01053 -0.0917 0.6493 1.0000
2.500 0.6945 0.01923 0.01066 -0.0895 0.6438 1.0000
2.750 0.7180 0.01920 0.01056 -0.0888 0.6401 1.0000
3.000 0.7298 0.01959 0.01095 -0.0865 0.6337 1.0000
3.250 0.7495 0.01981 0.01115 -0.0853 0.6282 1.0000
3.500 0.7775 0.01980 0.01110 -0.0854 0.6245 1.0000
3.750 0.7948 0.02020 0.01151 -0.0840 0.6184 1.0000
4.000 0.8156 0.02048 0.01181 -0.0831 0.6127 1.0000
4.250 0.8450 0.02049 0.01178 -0.0834 0.6089 1.0000
4.500 0.8633 0.02090 0.01223 -0.0822 0.6026 1.0000
4.750 0.8845 0.02120 0.01255 -0.0813 0.5966 1.0000
5.000 0.9153 0.02118 0.01252 -0.0818 0.5927 1.0000
5.250 0.9303 0.02172 0.01312 -0.0801 0.5856 1.0000
5.500 0.9539 0.02193 0.01337 -0.0796 0.5798 1.0000
5.750 0.9873 0.02183 0.01327 -0.0804 0.5759 1.0000
6.000 0.9959 0.02258 0.01412 -0.0779 0.5676 1.0000
6.250 1.0240 0.02264 0.01421 -0.0780 0.5625 1.0000
6.500 1.0446 0.02299 0.01463 -0.0771 0.5563 1.0000
6.750 1.0616 0.02344 0.01515 -0.0757 0.5493 1.0000
7.000 1.0959 0.02329 0.01502 -0.0765 0.5447 1.0000
7.250 1.1007 0.02409 0.01594 -0.0735 0.5355 1.0000
7.500 1.1339 0.02391 0.01579 -0.0741 0.5294 1.0000
7.750 1.1365 0.02470 0.01669 -0.0707 0.5202 1.0000
8.000 1.1675 0.02461 0.01664 -0.0711 0.5139 1.0000
8.250 1.1698 0.02551 0.01765 -0.0678 0.5049 1.0000
8.500 1.1993 0.02543 0.01762 -0.0679 0.4980 1.0000
8.750 1.2004 0.02644 0.01875 -0.0647 0.4883 1.0000
9.000 1.2237 0.02651 0.01887 -0.0639 0.4795 1.0000
9.250 1.2343 0.02699 0.01941 -0.0618 0.4670 1.0000
9.500 1.2386 0.02779 0.02025 -0.0591 0.4526 1.0000
9.750 1.2453 0.02854 0.02102 -0.0567 0.4371 1.0000
10.000 1.2514 0.02944 0.02195 -0.0545 0.4212 1.0000
10.250 1.2568 0.03048 0.02302 -0.0524 0.4052 1.0000
10.500 1.2618 0.03165 0.02422 -0.0503 0.3888 1.0000
10.750 1.2649 0.03303 0.02562 -0.0484 0.3716 1.0000
11.000 1.2663 0.03463 0.02724 -0.0464 0.3529 1.0000
11.250 1.2677 0.03631 0.02891 -0.0446 0.3327 1.0000
11.500 1.2684 0.03810 0.03063 -0.0429 0.3108 1.0000
11.750 1.2668 0.04021 0.03270 -0.0413 0.2875 1.0000
12.000 1.2641 0.04250 0.03490 -0.0397 0.2641 1.0000
12.250 1.2596 0.04510 0.03742 -0.0383 0.2396 1.0000
12.500 1.2542 0.04795 0.04017 -0.0372 0.2161 1.0000
12.750 1.2472 0.05109 0.04320 -0.0362 0.1937 1.0000
13.000 1.2410 0.05436 0.04639 -0.0355 0.1718 1.0000
13.250 1.2340 0.05783 0.04979 -0.0349 0.1515 1.0000
13.500 1.2275 0.06140 0.05328 -0.0346 0.1339 1.0000
13.750 1.2218 0.06501 0.05684 -0.0344 0.1183 1.0000
14.000 1.2167 0.06865 0.06045 -0.0344 0.1056 1.0000
14.250 1.2118 0.07236 0.06412 -0.0345 0.0956 1.0000
14.500 1.2097 0.07580 0.06760 -0.0347 0.0870 1.0000
14.750 1.2077 0.07931 0.07114 -0.0350 0.0801 1.0000
15.000 1.2057 0.08286 0.07472 -0.0354 0.0745 1.0000
15.250 1.2057 0.08618 0.07809 -0.0358 0.0696 1.0000
15.500 1.2061 0.08950 0.08147 -0.0362 0.0652 1.0000
15.750 1.2055 0.09293 0.08489 -0.0368 0.0618 1.0000
16.000 1.2095 0.09578 0.08787 -0.0372 0.0582 1.0000
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