I.S.A. 962 (isa962-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: I.S.A. 962 (isa962-il) Reynolds number: 500,000 Max Cl/Cd: 88.29 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-isa962-il-500000-n5.txt Download as CSV file: xf-isa962-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3276 0.10255 0.10011 -0.0280 1.0000 0.0229
-10.250 -0.3235 0.09930 0.09688 -0.0293 1.0000 0.0226
-10.000 -0.3298 0.09419 0.09179 -0.0330 1.0000 0.0238
-9.750 -0.3177 0.09110 0.08871 -0.0350 0.9923 0.0237
-9.500 -0.3038 0.08773 0.08533 -0.0380 0.9748 0.0235
-9.250 -0.2902 0.08367 0.08125 -0.0423 0.9536 0.0233
-9.000 -0.2795 0.07958 0.07712 -0.0465 0.9343 0.0233
-8.750 -0.2733 0.07573 0.07321 -0.0500 0.9187 0.0233
-8.500 -0.2683 0.06625 0.06362 -0.0627 0.9050 0.0241
-8.250 -0.2541 0.06133 0.05862 -0.0682 0.8965 0.0241
-8.000 -0.2377 0.05602 0.05322 -0.0740 0.8883 0.0241
-7.750 -0.2194 0.05026 0.04733 -0.0799 0.8811 0.0242
-7.500 -0.1995 0.04368 0.04057 -0.0859 0.8733 0.0242
-7.250 -0.1783 0.03773 0.03438 -0.0904 0.8663 0.0245
-7.000 -0.1551 0.03524 0.03177 -0.0918 0.8582 0.0247
-6.750 -0.1382 0.02421 0.01988 -0.0960 0.8515 0.0252
-6.500 -0.1149 0.02128 0.01655 -0.0964 0.8428 0.0254
-6.250 -0.0903 0.01935 0.01427 -0.0963 0.8344 0.0257
-6.000 -0.0647 0.01786 0.01250 -0.0962 0.8245 0.0259
-5.750 -0.0385 0.01667 0.01105 -0.0960 0.8160 0.0262
-5.500 -0.0118 0.01567 0.00983 -0.0957 0.8066 0.0264
-5.250 0.0151 0.01484 0.00879 -0.0955 0.7953 0.0267
-5.000 0.0421 0.01421 0.00797 -0.0952 0.7823 0.0271
-4.750 0.0692 0.01365 0.00722 -0.0948 0.7689 0.0276
-4.500 0.0966 0.01312 0.00653 -0.0946 0.7570 0.0278
-4.250 0.1242 0.01265 0.00592 -0.0943 0.7455 0.0280
-4.000 0.1517 0.01228 0.00542 -0.0940 0.7329 0.0283
-3.750 0.1792 0.01197 0.00499 -0.0937 0.7203 0.0284
-3.500 0.2066 0.01147 0.00441 -0.0935 0.7089 0.0288
-3.250 0.2340 0.01113 0.00401 -0.0933 0.6975 0.0292
-3.000 0.2615 0.01089 0.00372 -0.0931 0.6848 0.0296
-2.500 0.3165 0.01054 0.00324 -0.0926 0.6565 0.0305
-2.250 0.3440 0.01040 0.00304 -0.0923 0.6415 0.0310
-2.000 0.3716 0.01028 0.00287 -0.0921 0.6276 0.0316
-1.750 0.3993 0.01020 0.00273 -0.0919 0.6142 0.0325
-1.500 0.4269 0.01014 0.00260 -0.0917 0.6004 0.0333
-1.250 0.4544 0.01006 0.00247 -0.0915 0.5862 0.0339
-1.000 0.4820 0.00997 0.00234 -0.0914 0.5721 0.0348
-0.750 0.5097 0.00993 0.00226 -0.0912 0.5576 0.0359
-0.500 0.5371 0.00993 0.00221 -0.0910 0.5411 0.0373
-0.250 0.5644 0.00997 0.00217 -0.0908 0.5231 0.0389
0.000 0.5915 0.01002 0.00215 -0.0905 0.5027 0.0413
0.500 0.6433 0.01024 0.00225 -0.0898 0.4306 0.0978
0.750 0.6689 0.01045 0.00236 -0.0894 0.3937 0.1229
1.000 0.6948 0.01056 0.00249 -0.0892 0.3693 0.1753
1.250 0.7209 0.01054 0.00266 -0.0890 0.3528 0.2836
1.500 0.7467 0.01042 0.00283 -0.0888 0.3400 0.4300
2.000 0.8029 0.00961 0.00315 -0.0891 0.3164 1.0000
2.250 0.8291 0.00983 0.00328 -0.0888 0.3065 1.0000
2.500 0.8560 0.00999 0.00340 -0.0886 0.2992 1.0000
2.750 0.8821 0.01023 0.00356 -0.0882 0.2891 1.0000
3.000 0.9086 0.01041 0.00370 -0.0880 0.2787 1.0000
3.250 0.9348 0.01063 0.00386 -0.0877 0.2670 1.0000
3.500 0.9606 0.01088 0.00402 -0.0874 0.2511 1.0000
3.750 0.9856 0.01119 0.00421 -0.0870 0.2281 1.0000
4.000 1.0093 0.01164 0.00447 -0.0865 0.1956 1.0000
4.250 1.0332 0.01207 0.00477 -0.0859 0.1774 1.0000
4.500 1.0574 0.01244 0.00506 -0.0854 0.1672 1.0000
4.750 1.0825 0.01272 0.00532 -0.0850 0.1616 1.0000
5.000 1.1069 0.01305 0.00562 -0.0845 0.1562 1.0000
5.250 1.1314 0.01337 0.00591 -0.0841 0.1514 1.0000
5.500 1.1564 0.01362 0.00618 -0.0837 0.1480 1.0000
5.750 1.1808 0.01392 0.00648 -0.0832 0.1442 1.0000
6.000 1.2046 0.01426 0.00681 -0.0827 0.1400 1.0000
6.250 1.2282 0.01461 0.00715 -0.0821 0.1363 1.0000
6.500 1.2526 0.01487 0.00745 -0.0817 0.1339 1.0000
6.750 1.2765 0.01517 0.00777 -0.0812 0.1308 1.0000
7.000 1.2996 0.01551 0.00811 -0.0806 0.1265 1.0000
7.250 1.3219 0.01591 0.00850 -0.0799 0.1217 1.0000
7.500 1.3452 0.01621 0.00882 -0.0793 0.1173 1.0000
7.750 1.3674 0.01658 0.00918 -0.0786 0.1123 1.0000
8.000 1.3888 0.01699 0.00958 -0.0778 0.1079 1.0000
8.250 1.4106 0.01735 0.00998 -0.0771 0.1039 1.0000
8.500 1.4312 0.01778 0.01040 -0.0762 0.0992 1.0000
8.750 1.4511 0.01824 0.01085 -0.0752 0.0944 1.0000
9.000 1.4704 0.01869 0.01132 -0.0741 0.0898 1.0000
9.250 1.4879 0.01922 0.01184 -0.0727 0.0856 1.0000
9.500 1.5045 0.01970 0.01236 -0.0711 0.0823 1.0000
9.750 1.5201 0.02025 0.01293 -0.0695 0.0783 1.0000
10.000 1.5341 0.02092 0.01359 -0.0677 0.0741 1.0000
10.250 1.5495 0.02151 0.01423 -0.0662 0.0708 1.0000
10.500 1.5635 0.02221 0.01496 -0.0646 0.0669 1.0000
10.750 1.5765 0.02301 0.01578 -0.0629 0.0632 1.0000
11.000 1.5888 0.02388 0.01666 -0.0613 0.0578 1.0000
11.250 1.5996 0.02489 0.01768 -0.0597 0.0525 1.0000
11.500 1.6081 0.02611 0.01888 -0.0579 0.0452 1.0000
11.750 1.6046 0.02831 0.02095 -0.0552 0.0246 1.0000
12.000 1.6018 0.03057 0.02320 -0.0528 0.0174 1.0000
12.250 1.6067 0.03228 0.02497 -0.0513 0.0158 1.0000
12.500 1.6112 0.03407 0.02685 -0.0499 0.0148 1.0000
12.750 1.6167 0.03583 0.02871 -0.0488 0.0141 1.0000
13.000 1.6220 0.03767 0.03066 -0.0477 0.0136 1.0000
13.250 1.6258 0.03972 0.03280 -0.0468 0.0131 1.0000
13.500 1.6281 0.04198 0.03517 -0.0460 0.0127 1.0000
13.750 1.6287 0.04451 0.03781 -0.0454 0.0123 1.0000
14.000 1.6272 0.04735 0.04076 -0.0449 0.0119 1.0000
14.250 1.6233 0.05054 0.04408 -0.0445 0.0116 1.0000
14.500 1.6218 0.05359 0.04725 -0.0444 0.0114 1.0000
14.750 1.6196 0.05684 0.05062 -0.0445 0.0112 1.0000
15.000 1.6156 0.06041 0.05432 -0.0448 0.0109 1.0000
15.250 1.6098 0.06436 0.05839 -0.0454 0.0107 1.0000
15.500 1.6023 0.06866 0.06282 -0.0462 0.0106 1.0000
15.750 1.5927 0.07340 0.06771 -0.0472 0.0104 1.0000
16.000 1.5812 0.07855 0.07299 -0.0486 0.0103 1.0000
16.250 1.5677 0.08420 0.07878 -0.0503 0.0102 1.0000
16.500 1.5522 0.09035 0.08509 -0.0523 0.0101 1.0000
16.750 1.5348 0.09694 0.09183 -0.0546 0.0100 1.0000
17.000 1.5161 0.10395 0.09899 -0.0573 0.0100 1.0000
17.250 1.4961 0.11131 0.10651 -0.0602 0.0099 1.0000
17.500 1.4754 0.11884 0.11418 -0.0633 0.0099 1.0000
17.750 1.4540 0.12667 0.12215 -0.0668 0.0099 1.0000
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Polar data table (+)
Polar graphs
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