I.S.A. 960 (isa960-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: I.S.A. 960 (isa960-il) Reynolds number: 100,000 Max Cl/Cd: 49.75 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-isa960-il-100000-n5.txt Download as CSV file: xf-isa960-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: I.S.A. 960
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3361 0.09252 0.08802 -0.0355 1.0000 0.0319
-9.000 -0.3432 0.08999 0.08559 -0.0347 1.0000 0.0315
-8.750 -0.3553 0.08794 0.08365 -0.0328 1.0000 0.0312
-8.500 -0.3685 0.08589 0.08172 -0.0310 1.0000 0.0309
-8.250 -0.3609 0.08121 0.07706 -0.0359 0.9947 0.0306
-8.000 -0.3389 0.07461 0.07042 -0.0452 0.9849 0.0303
-7.750 -0.3153 0.06748 0.06322 -0.0551 0.9747 0.0302
-7.500 -0.2896 0.05964 0.05524 -0.0653 0.9645 0.0308
-7.250 -0.2633 0.04952 0.04482 -0.0763 0.9545 0.0322
-7.000 -0.2371 0.03404 0.02816 -0.0878 0.9482 0.0332
-6.750 -0.2058 0.02828 0.02151 -0.0914 0.9393 0.0347
-6.500 -0.1706 0.02680 0.01986 -0.0935 0.9288 0.0382
-6.250 -0.1333 0.02395 0.01636 -0.0958 0.9202 0.0423
-6.000 -0.1018 0.02241 0.01452 -0.0966 0.9086 0.0458
-5.750 -0.0688 0.02156 0.01345 -0.0974 0.8949 0.0516
-5.500 -0.0376 0.02057 0.01225 -0.0977 0.8788 0.0564
-5.250 -0.0079 0.01981 0.01118 -0.0977 0.8619 0.0648
-5.000 0.0199 0.01909 0.01031 -0.0973 0.8459 0.0731
-4.750 0.0468 0.01845 0.00956 -0.0969 0.8299 0.0844
-4.500 0.0738 0.01807 0.00908 -0.0965 0.8127 0.0976
-4.250 0.1014 0.01776 0.00862 -0.0961 0.7945 0.1082
-4.000 0.1295 0.01751 0.00814 -0.0957 0.7753 0.1183
-3.750 0.1577 0.01737 0.00776 -0.0954 0.7558 0.1284
-3.500 0.1853 0.01734 0.00757 -0.0951 0.7363 0.1413
-3.250 0.2124 0.01710 0.00718 -0.0947 0.7167 0.1499
-3.000 0.2392 0.01681 0.00667 -0.0941 0.6932 0.1557
-2.750 0.2654 0.01652 0.00624 -0.0935 0.6667 0.1611
-2.500 0.2917 0.01626 0.00590 -0.0931 0.6428 0.1680
-2.250 0.3180 0.01604 0.00557 -0.0926 0.6176 0.1766
-2.000 0.3442 0.01589 0.00531 -0.0921 0.5888 0.1878
-1.750 0.3698 0.01580 0.00508 -0.0915 0.5567 0.2021
-1.500 0.3949 0.01580 0.00491 -0.0909 0.5240 0.2201
-1.250 0.4202 0.01581 0.00481 -0.0904 0.4932 0.2434
-1.000 0.4459 0.01581 0.00474 -0.0900 0.4646 0.2795
-0.750 0.4714 0.01563 0.00472 -0.0897 0.4385 0.3610
-0.500 0.4997 0.01433 0.00471 -0.0893 0.4069 1.0000
-0.250 0.5202 0.01513 0.00482 -0.0882 0.3043 1.0000
0.000 0.5436 0.01568 0.00495 -0.0875 0.2669 1.0000
0.250 0.5687 0.01601 0.00506 -0.0871 0.2531 1.0000
0.500 0.5942 0.01628 0.00518 -0.0867 0.2453 1.0000
0.750 0.6200 0.01652 0.00530 -0.0864 0.2403 1.0000
1.000 0.6456 0.01676 0.00544 -0.0861 0.2359 1.0000
1.250 0.6712 0.01700 0.00561 -0.0857 0.2324 1.0000
1.500 0.6970 0.01722 0.00577 -0.0854 0.2293 1.0000
1.750 0.7226 0.01745 0.00596 -0.0851 0.2264 1.0000
2.000 0.7480 0.01770 0.00618 -0.0847 0.2237 1.0000
2.250 0.7733 0.01795 0.00641 -0.0844 0.2214 1.0000
2.500 0.7984 0.01822 0.00666 -0.0840 0.2193 1.0000
2.750 0.8237 0.01846 0.00693 -0.0836 0.2176 1.0000
3.000 0.8489 0.01871 0.00721 -0.0833 0.2158 1.0000
3.250 0.8739 0.01898 0.00750 -0.0829 0.2139 1.0000
3.500 0.8985 0.01928 0.00784 -0.0825 0.2101 1.0000
3.750 0.9229 0.01958 0.00818 -0.0820 0.2076 1.0000
4.000 0.9470 0.01991 0.00855 -0.0815 0.2054 1.0000
4.250 0.9710 0.02024 0.00896 -0.0810 0.2033 1.0000
4.500 0.9953 0.02054 0.00935 -0.0805 0.2005 1.0000
4.750 1.0192 0.02086 0.00976 -0.0800 0.1968 1.0000
5.000 1.0427 0.02121 0.01021 -0.0795 0.1932 1.0000
5.250 1.0658 0.02160 0.01070 -0.0788 0.1898 1.0000
5.500 1.0890 0.02196 0.01118 -0.0783 0.1840 1.0000
5.750 1.1119 0.02235 0.01170 -0.0776 0.1763 1.0000
6.000 1.1339 0.02279 0.01224 -0.0769 0.1667 1.0000
6.250 1.1548 0.02331 0.01282 -0.0760 0.1605 1.0000
6.500 1.1754 0.02384 0.01341 -0.0751 0.1572 1.0000
6.750 1.1957 0.02437 0.01403 -0.0742 0.1552 1.0000
7.000 1.2157 0.02492 0.01469 -0.0732 0.1540 1.0000
7.250 1.2351 0.02549 0.01537 -0.0721 0.1531 1.0000
7.500 1.2536 0.02612 0.01613 -0.0710 0.1518 1.0000
7.750 1.2683 0.02695 0.01692 -0.0694 0.1468 1.0000
8.000 1.2775 0.02809 0.01795 -0.0672 0.1402 1.0000
8.250 1.2822 0.02954 0.01932 -0.0644 0.1339 1.0000
8.500 1.2898 0.03091 0.02071 -0.0621 0.1288 1.0000
8.750 1.2979 0.03234 0.02218 -0.0600 0.1245 1.0000
9.000 1.3071 0.03386 0.02371 -0.0581 0.1203 1.0000
9.250 1.3165 0.03537 0.02535 -0.0564 0.1146 1.0000
9.500 1.3253 0.03700 0.02708 -0.0547 0.1085 1.0000
9.750 1.3341 0.03862 0.02877 -0.0532 0.1023 1.0000
10.000 1.3384 0.03992 0.03050 -0.0514 0.0965 1.0000
10.250 1.3589 0.04000 0.03138 -0.0510 0.0579 1.0000
10.500 1.3581 0.04220 0.03327 -0.0498 0.0397 1.0000
10.750 1.3561 0.04482 0.03593 -0.0482 0.0310 1.0000
11.000 1.3550 0.04746 0.03864 -0.0469 0.0270 1.0000
11.250 1.3521 0.05038 0.04165 -0.0459 0.0250 1.0000
11.500 1.3490 0.05343 0.04484 -0.0451 0.0238 1.0000
11.750 1.3450 0.05671 0.04831 -0.0446 0.0228 1.0000
12.000 1.3392 0.06032 0.05211 -0.0444 0.0221 1.0000
12.250 1.3316 0.06430 0.05631 -0.0446 0.0213 1.0000
12.500 1.3223 0.06868 0.06088 -0.0451 0.0207 1.0000
12.750 1.3113 0.07349 0.06587 -0.0460 0.0203 1.0000
13.000 1.2990 0.07879 0.07135 -0.0474 0.0198 1.0000
13.250 1.2854 0.08458 0.07732 -0.0492 0.0195 1.0000
13.500 1.2712 0.09072 0.08362 -0.0514 0.0192 1.0000
13.750 1.2566 0.09716 0.09023 -0.0538 0.0190 1.0000
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Polar data table (+)
Polar graphs
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