Fage & Collins 2 (fg2-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: Fage & Collins 2 (fg2-il) Reynolds number: 500,000 Max Cl/Cd: 93.71 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fg2-il-500000.txt Download as CSV file: xf-fg2-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: Fage & Collins 2
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3314 0.08663 0.08454 -0.0214 1.0000 0.0167
-8.750 -0.3298 0.08344 0.08137 -0.0211 1.0000 0.0169
-8.500 -0.4262 0.09237 0.09019 -0.0215 1.0000 0.0162
-8.250 -0.4321 0.08949 0.08736 -0.0219 1.0000 0.0162
-8.000 -0.4361 0.08548 0.08337 -0.0195 1.0000 0.0165
-7.750 -0.4386 0.08285 0.08078 -0.0185 1.0000 0.0167
-7.500 -0.4381 0.07965 0.07759 -0.0192 1.0000 0.0168
-7.250 -0.4370 0.07671 0.07466 -0.0192 1.0000 0.0170
-7.000 -0.4360 0.07345 0.07140 -0.0200 1.0000 0.0171
-6.750 -0.4342 0.07045 0.06841 -0.0202 1.0000 0.0174
-6.500 -0.4325 0.06736 0.06530 -0.0202 1.0000 0.0176
-6.250 -0.4303 0.06430 0.06221 -0.0199 1.0000 0.0181
-6.000 -0.4009 0.05927 0.05707 -0.0259 0.9970 0.0189
-5.750 -0.3539 0.05267 0.05012 -0.0341 0.9930 0.0210
-5.500 -0.3236 0.04785 0.04505 -0.0373 0.9887 0.0211
-5.250 -0.2922 0.04304 0.03994 -0.0403 0.9853 0.0211
-5.000 -0.2776 0.03789 0.03480 -0.0420 0.9803 0.0221
-4.750 -0.2491 0.03536 0.03216 -0.0439 0.9759 0.0230
-4.500 -0.2159 0.03247 0.02907 -0.0460 0.9730 0.0248
-4.250 -0.1836 0.03120 0.02732 -0.0448 0.9649 0.0276
-3.750 -0.1395 0.02358 0.01927 -0.0445 0.9512 0.0296
-3.500 -0.1121 0.02194 0.01750 -0.0448 0.9449 0.0310
-3.250 -0.0841 0.02066 0.01600 -0.0443 0.9368 0.0343
-3.000 -0.0510 0.02123 0.01627 -0.0441 0.9281 0.0364
-2.750 -0.0243 0.01701 0.01188 -0.0449 0.9218 0.0401
-2.500 0.0132 0.01622 0.01093 -0.0467 0.9129 0.0453
-2.250 0.0586 0.01451 0.00903 -0.0507 0.9045 0.0526
-2.000 0.1132 0.01348 0.00785 -0.0569 0.8914 0.0655
-1.750 0.1568 0.01275 0.00703 -0.0608 0.8677 0.0819
-1.250 0.2282 0.01117 0.00475 -0.0616 0.7924 0.0482
-1.000 0.2511 0.01044 0.00381 -0.0602 0.7408 0.0450
-0.750 0.2713 0.01018 0.00334 -0.0582 0.6977 0.0439
-0.500 0.2920 0.01004 0.00303 -0.0565 0.6654 0.0444
-0.250 0.3130 0.00986 0.00271 -0.0548 0.6405 0.0434
0.000 0.3347 0.00971 0.00244 -0.0533 0.6194 0.0427
0.500 0.3793 0.00953 0.00207 -0.0507 0.5820 0.0432
0.750 0.4022 0.00950 0.00195 -0.0495 0.5629 0.0439
1.000 0.4253 0.00950 0.00186 -0.0484 0.5448 0.0450
1.250 0.4488 0.00952 0.00179 -0.0474 0.5279 0.0461
1.500 0.4726 0.00957 0.00176 -0.0464 0.5117 0.0480
1.750 0.4965 0.00961 0.00174 -0.0455 0.4947 0.0517
2.000 0.6636 0.00806 0.00231 -0.0784 0.4457 1.0000
2.250 0.6863 0.00823 0.00236 -0.0774 0.4262 1.0000
2.500 0.7091 0.00840 0.00243 -0.0763 0.4084 1.0000
2.750 0.7322 0.00857 0.00252 -0.0753 0.3933 1.0000
3.000 0.7552 0.00874 0.00262 -0.0743 0.3804 1.0000
3.250 0.7786 0.00890 0.00274 -0.0734 0.3693 1.0000
3.500 0.8021 0.00906 0.00286 -0.0725 0.3601 1.0000
4.000 0.8490 0.00938 0.00317 -0.0708 0.3442 1.0000
4.250 0.8720 0.00957 0.00333 -0.0698 0.3353 1.0000
4.500 0.8950 0.00976 0.00348 -0.0689 0.3233 1.0000
4.750 0.9184 0.00992 0.00366 -0.0680 0.3117 1.0000
5.000 0.9416 0.01010 0.00382 -0.0671 0.2993 1.0000
5.250 0.9643 0.01030 0.00399 -0.0662 0.2824 1.0000
5.500 0.9868 0.01053 0.00417 -0.0652 0.2636 1.0000
5.750 1.0083 0.01083 0.00437 -0.0641 0.2292 1.0000
6.000 1.0245 0.01158 0.00478 -0.0621 0.1687 1.0000
6.250 1.0425 0.01221 0.00524 -0.0604 0.1396 1.0000
6.500 1.0609 0.01279 0.00568 -0.0587 0.1134 1.0000
6.750 1.0727 0.01393 0.00640 -0.0560 0.0454 1.0000
7.000 1.0871 0.01484 0.00719 -0.0535 0.0219 1.0000
7.250 1.1051 0.01544 0.00787 -0.0517 0.0186 1.0000
7.500 1.1230 0.01604 0.00858 -0.0498 0.0172 1.0000
7.750 1.1402 0.01666 0.00931 -0.0479 0.0162 1.0000
8.000 1.1562 0.01736 0.01010 -0.0457 0.0154 1.0000
8.250 1.1704 0.01815 0.01099 -0.0433 0.0148 1.0000
8.500 1.1837 0.01897 0.01191 -0.0408 0.0144 1.0000
8.750 1.1928 0.02002 0.01306 -0.0376 0.0137 1.0000
9.000 1.1957 0.02146 0.01460 -0.0334 0.0130 1.0000
9.250 1.1986 0.02285 0.01610 -0.0293 0.0128 1.0000
9.500 1.2027 0.02390 0.01725 -0.0253 0.0123 1.0000
9.750 1.2068 0.02494 0.01839 -0.0214 0.0121 1.0000
10.000 1.2145 0.02580 0.01934 -0.0183 0.0117 1.0000
10.250 1.2178 0.02716 0.02081 -0.0148 0.0118 1.0000
10.500 1.2238 0.02834 0.02208 -0.0118 0.0114 1.0000
10.750 1.2285 0.02979 0.02365 -0.0089 0.0112 1.0000
11.000 1.2333 0.03136 0.02533 -0.0062 0.0110 1.0000
11.250 1.2376 0.03317 0.02726 -0.0037 0.0109 1.0000
11.500 1.2420 0.03508 0.02931 -0.0014 0.0110 1.0000
11.750 1.2448 0.03701 0.03137 0.0007 0.0106 1.0000
12.000 1.2466 0.03952 0.03407 0.0028 0.0108 1.0000
12.250 1.2461 0.04203 0.03676 0.0046 0.0108 1.0000
12.500 1.2434 0.04494 0.03986 0.0063 0.0109 1.0000
12.750 1.2398 0.04764 0.04275 0.0074 0.0108 1.0000
13.000 1.2332 0.05093 0.04622 0.0081 0.0108 1.0000
13.250 1.2175 0.05626 0.05182 0.0088 0.0116 1.0000
13.500 1.2080 0.05992 0.05566 0.0082 0.0113 1.0000
13.750 1.2097 0.06191 0.05767 0.0070 0.0102 1.0000
14.000 1.1918 0.06761 0.06362 0.0055 0.0106 1.0000
14.250 1.1737 0.07362 0.06984 0.0034 0.0110 1.0000
14.500 1.1535 0.08019 0.07660 0.0007 0.0112 1.0000
14.750 1.1337 0.08696 0.08354 -0.0022 0.0116 1.0000
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Polar data table (+)
Polar graphs
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