I.S.A. 962 (isa962-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: I.S.A. 962 (isa962-il) Reynolds number: 1,000,000 Max Cl/Cd: 102.54 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-isa962-il-1000000-n5.txt Download as CSV file: xf-isa962-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3490 0.09149 0.08963 -0.0365 0.9343 0.0172
-10.250 -0.3417 0.08907 0.08712 -0.0374 0.9153 0.0173
-9.250 -0.4016 0.02823 0.02525 -0.0944 0.8720 0.0206
-9.000 -0.3829 0.02428 0.02092 -0.0959 0.8670 0.0208
-8.750 -0.3600 0.02228 0.01871 -0.0963 0.8621 0.0209
-8.500 -0.3362 0.02071 0.01692 -0.0964 0.8569 0.0211
-8.250 -0.3117 0.01943 0.01545 -0.0964 0.8516 0.0212
-8.000 -0.2866 0.01819 0.01402 -0.0964 0.8450 0.0214
-7.750 -0.2613 0.01711 0.01274 -0.0962 0.8375 0.0215
-7.500 -0.2354 0.01614 0.01160 -0.0960 0.8297 0.0217
-7.250 -0.2094 0.01524 0.01051 -0.0958 0.8201 0.0219
-7.000 -0.1828 0.01446 0.00957 -0.0956 0.8088 0.0221
-6.750 -0.1561 0.01376 0.00871 -0.0953 0.7986 0.0222
-6.500 -0.1292 0.01314 0.00793 -0.0951 0.7872 0.0224
-6.250 -0.1021 0.01258 0.00723 -0.0948 0.7739 0.0226
-6.000 -0.0749 0.01209 0.00659 -0.0946 0.7590 0.0228
-5.750 -0.0477 0.01167 0.00604 -0.0943 0.7436 0.0230
-5.500 -0.0202 0.01129 0.00553 -0.0941 0.7300 0.0232
-5.250 0.0075 0.01098 0.00511 -0.0939 0.7187 0.0234
-5.000 0.0354 0.01074 0.00478 -0.0937 0.7072 0.0236
-4.750 0.0634 0.01051 0.00447 -0.0935 0.6956 0.0238
-4.500 0.0912 0.01028 0.00416 -0.0934 0.6827 0.0239
-4.250 0.1191 0.01009 0.00388 -0.0932 0.6702 0.0240
-4.000 0.1469 0.00966 0.00338 -0.0930 0.6597 0.0244
-3.750 0.1748 0.00943 0.00310 -0.0929 0.6491 0.0248
-3.500 0.2027 0.00929 0.00289 -0.0927 0.6338 0.0250
-3.250 0.2306 0.00918 0.00272 -0.0926 0.6194 0.0253
-3.000 0.2588 0.00906 0.00256 -0.0925 0.6072 0.0256
-2.750 0.2868 0.00898 0.00241 -0.0923 0.5923 0.0259
-2.500 0.3146 0.00893 0.00229 -0.0922 0.5745 0.0263
-2.250 0.3425 0.00888 0.00217 -0.0920 0.5574 0.0266
-2.000 0.3705 0.00883 0.00206 -0.0919 0.5423 0.0271
-1.750 0.3985 0.00880 0.00197 -0.0918 0.5266 0.0275
-1.500 0.4263 0.00880 0.00190 -0.0917 0.5079 0.0279
-1.250 0.4539 0.00884 0.00186 -0.0915 0.4875 0.0283
-1.000 0.4814 0.00888 0.00180 -0.0914 0.4629 0.0290
-0.750 0.5081 0.00901 0.00179 -0.0911 0.4259 0.0300
-0.500 0.5342 0.00925 0.00184 -0.0908 0.3798 0.0308
-0.250 0.5611 0.00941 0.00188 -0.0905 0.3533 0.0317
0.000 0.5884 0.00951 0.00192 -0.0904 0.3368 0.0327
0.500 0.6438 0.00963 0.00198 -0.0902 0.3174 0.0366
0.750 0.6715 0.00968 0.00202 -0.0901 0.3101 0.0423
1.000 0.6991 0.00964 0.00210 -0.0901 0.3035 0.0969
1.250 0.7267 0.00969 0.00217 -0.0900 0.2951 0.1126
1.500 0.7541 0.00975 0.00225 -0.0899 0.2873 0.1362
1.750 0.7815 0.00964 0.00237 -0.0900 0.2805 0.2398
2.000 0.8085 0.00963 0.00250 -0.0899 0.2706 0.3291
2.250 0.8349 0.00944 0.00266 -0.0899 0.2587 0.5008
2.750 0.8883 0.00893 0.00300 -0.0897 0.2117 1.0000
3.000 0.9126 0.00937 0.00325 -0.0892 0.1779 1.0000
3.250 0.9385 0.00964 0.00344 -0.0889 0.1665 1.0000
3.500 0.9648 0.00986 0.00360 -0.0887 0.1601 1.0000
3.750 0.9909 0.01010 0.00379 -0.0884 0.1535 1.0000
4.000 1.0175 0.01027 0.00395 -0.0882 0.1504 1.0000
4.250 1.0439 0.01045 0.00412 -0.0880 0.1470 1.0000
4.500 1.0700 0.01067 0.00430 -0.0878 0.1429 1.0000
4.750 1.0958 0.01090 0.00451 -0.0875 0.1387 1.0000
5.000 1.1219 0.01109 0.00470 -0.0873 0.1359 1.0000
5.250 1.1481 0.01128 0.00488 -0.0871 0.1333 1.0000
5.500 1.1739 0.01149 0.00508 -0.0868 0.1304 1.0000
5.750 1.1994 0.01172 0.00530 -0.0866 0.1272 1.0000
6.000 1.2245 0.01198 0.00554 -0.0862 0.1232 1.0000
6.250 1.2500 0.01219 0.00575 -0.0860 0.1198 1.0000
6.500 1.2748 0.01246 0.00599 -0.0856 0.1141 1.0000
6.750 1.2990 0.01277 0.00625 -0.0852 0.1084 1.0000
7.000 1.3238 0.01301 0.00650 -0.0848 0.1048 1.0000
7.250 1.3476 0.01333 0.00679 -0.0844 0.0996 1.0000
7.500 1.3713 0.01365 0.00709 -0.0839 0.0946 1.0000
7.750 1.3947 0.01397 0.00740 -0.0834 0.0900 1.0000
8.000 1.4173 0.01435 0.00774 -0.0827 0.0850 1.0000
8.250 1.4400 0.01469 0.00809 -0.0821 0.0805 1.0000
8.500 1.4612 0.01514 0.00849 -0.0813 0.0747 1.0000
8.750 1.4832 0.01551 0.00886 -0.0806 0.0710 1.0000
9.000 1.5037 0.01596 0.00930 -0.0797 0.0664 1.0000
9.250 1.5241 0.01640 0.00973 -0.0787 0.0624 1.0000
9.500 1.5429 0.01692 0.01023 -0.0776 0.0571 1.0000
9.750 1.5607 0.01746 0.01075 -0.0762 0.0516 1.0000
10.000 1.5751 0.01813 0.01139 -0.0744 0.0446 1.0000
10.250 1.5769 0.01945 0.01256 -0.0706 0.0245 1.0000
10.500 1.5818 0.02067 0.01375 -0.0675 0.0156 1.0000
10.750 1.5943 0.02145 0.01457 -0.0656 0.0139 1.0000
11.000 1.6070 0.02223 0.01540 -0.0638 0.0130 1.0000
11.250 1.6188 0.02311 0.01633 -0.0621 0.0122 1.0000
11.500 1.6301 0.02406 0.01733 -0.0605 0.0115 1.0000
11.750 1.6425 0.02496 0.01829 -0.0591 0.0112 1.0000
12.000 1.6539 0.02595 0.01934 -0.0577 0.0107 1.0000
12.250 1.6643 0.02706 0.02051 -0.0563 0.0103 1.0000
12.500 1.6737 0.02828 0.02179 -0.0549 0.0099 1.0000
12.750 1.6817 0.02965 0.02321 -0.0535 0.0095 1.0000
13.000 1.6884 0.03117 0.02480 -0.0521 0.0091 1.0000
13.250 1.6960 0.03265 0.02635 -0.0510 0.0089 1.0000
13.500 1.7033 0.03420 0.02798 -0.0499 0.0087 1.0000
13.750 1.7096 0.03590 0.02975 -0.0490 0.0085 1.0000
14.000 1.7149 0.03776 0.03169 -0.0481 0.0084 1.0000
14.250 1.7189 0.03978 0.03379 -0.0473 0.0082 1.0000
14.500 1.7218 0.04199 0.03608 -0.0466 0.0080 1.0000
14.750 1.7235 0.04440 0.03857 -0.0461 0.0078 1.0000
15.000 1.7236 0.04703 0.04129 -0.0457 0.0076 1.0000
15.250 1.7224 0.04992 0.04427 -0.0454 0.0075 1.0000
15.500 1.7198 0.05309 0.04754 -0.0454 0.0074 1.0000
15.750 1.7156 0.05657 0.05112 -0.0455 0.0072 1.0000
16.000 1.7089 0.06048 0.05513 -0.0459 0.0071 1.0000
16.250 1.7002 0.06478 0.05954 -0.0465 0.0070 1.0000
16.500 1.6909 0.06932 0.06420 -0.0474 0.0069 1.0000
16.750 1.6821 0.07388 0.06887 -0.0484 0.0068 1.0000
17.000 1.6709 0.07889 0.07401 -0.0496 0.0068 1.0000
17.250 1.6578 0.08436 0.07960 -0.0512 0.0067 1.0000
17.500 1.6419 0.09041 0.08579 -0.0531 0.0067 1.0000
17.750 1.6243 0.09684 0.09235 -0.0553 0.0066 1.0000
18.000 1.6040 0.10389 0.09954 -0.0579 0.0066 1.0000
18.250 1.5828 0.11125 0.10705 -0.0608 0.0066 1.0000
18.500 1.5594 0.11904 0.11498 -0.0639 0.0066 1.0000
18.750 1.5358 0.12700 0.12308 -0.0674 0.0066 1.0000
19.000 1.5101 0.13554 0.13176 -0.0714 0.0066 1.0000
19.250 1.4869 0.14379 0.14015 -0.0754 0.0066 1.0000
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Polar data table (+)
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