Fage & Collins 3 (fg3-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: Fage & Collins 3 (fg3-il) Reynolds number: 500,000 Max Cl/Cd: 90.36 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fg3-il-500000.txt Download as CSV file: xf-fg3-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: Fage & Collins 3
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3440 0.10819 0.10604 -0.0304 1.0000 0.0159
-9.500 -0.3480 0.10552 0.10341 -0.0303 1.0000 0.0160
-9.250 -0.3613 0.10348 0.10142 -0.0288 1.0000 0.0160
-9.000 -0.3581 0.09935 0.09732 -0.0297 0.9991 0.0161
-8.750 -0.3440 0.09562 0.09358 -0.0307 0.9977 0.0163
-8.500 -0.3275 0.09196 0.08991 -0.0337 0.9957 0.0167
-8.250 -0.3131 0.08789 0.08585 -0.0383 0.9930 0.0168
-8.000 -0.2973 0.08425 0.08220 -0.0428 0.9893 0.0178
-7.750 -0.2813 0.07964 0.07759 -0.0496 0.9856 0.0181
-7.500 -0.2710 0.07550 0.07345 -0.0548 0.9777 0.0187
-7.250 -0.2497 0.06923 0.06711 -0.0651 0.9696 0.0199
-7.000 -0.2250 0.06276 0.06050 -0.0742 0.9628 0.0202
-6.750 -0.2092 0.05782 0.05540 -0.0775 0.9552 0.0203
-6.500 -0.1882 0.05300 0.05042 -0.0805 0.9508 0.0204
-6.250 -0.1790 0.04768 0.04505 -0.0817 0.9460 0.0208
-6.000 -0.1603 0.04499 0.04231 -0.0827 0.9406 0.0212
-5.750 -0.1338 0.04203 0.03925 -0.0852 0.9372 0.0219
-5.500 -0.1066 0.03883 0.03589 -0.0873 0.9323 0.0231
-5.250 -0.0672 0.03562 0.03212 -0.0889 0.9265 0.0258
-5.000 -0.0388 0.02949 0.02561 -0.0918 0.9226 0.0265
-4.750 -0.0125 0.02726 0.02330 -0.0930 0.9156 0.0271
-4.500 0.0202 0.02545 0.02136 -0.0952 0.9101 0.0284
-4.250 0.0484 0.02394 0.01961 -0.0954 0.9033 0.0312
-4.000 0.0699 0.02197 0.01704 -0.0932 0.8956 0.0339
-3.750 0.0918 0.02009 0.01513 -0.0928 0.8884 0.0350
-3.500 0.1154 0.01901 0.01394 -0.0922 0.8805 0.0366
-3.250 0.1362 0.01825 0.01302 -0.0905 0.8722 0.0395
-3.000 0.1582 0.01703 0.01148 -0.0890 0.8646 0.0446
-2.750 0.1769 0.01618 0.01063 -0.0872 0.8554 0.0471
-2.500 0.2019 0.01642 0.01071 -0.0861 0.8466 0.0532
-2.250 0.2198 0.01469 0.00888 -0.0843 0.8365 0.0590
-2.000 0.2409 0.01455 0.00867 -0.0826 0.8250 0.0653
-1.750 0.2610 0.01357 0.00763 -0.0811 0.8128 0.0760
-1.000 0.3378 0.01092 0.00440 -0.0771 0.7572 0.0474
-0.750 0.3595 0.01065 0.00393 -0.0753 0.7283 0.0440
-0.500 0.3786 0.01053 0.00364 -0.0731 0.6933 0.0435
-0.250 0.3942 0.01038 0.00330 -0.0703 0.6501 0.0437
0.000 0.4069 0.01048 0.00315 -0.0668 0.5958 0.0432
0.250 0.4194 0.01069 0.00310 -0.0634 0.5425 0.0427
0.500 0.4335 0.01073 0.00293 -0.0604 0.5025 0.0425
0.750 0.4500 0.01074 0.00278 -0.0579 0.4733 0.0425
1.000 0.4676 0.01072 0.00262 -0.0557 0.4506 0.0431
1.250 0.4867 0.01073 0.00251 -0.0538 0.4328 0.0440
1.500 0.5070 0.01078 0.00247 -0.0522 0.4179 0.0449
1.750 0.5280 0.01085 0.00245 -0.0508 0.4050 0.0468
2.000 0.5497 0.01091 0.00246 -0.0495 0.3938 0.0496
2.250 0.5713 0.01101 0.00250 -0.0482 0.3843 0.0526
2.500 0.7984 0.00999 0.00350 -0.0950 0.3564 1.0000
2.750 0.8207 0.01014 0.00360 -0.0939 0.3494 1.0000
3.000 0.8419 0.01035 0.00373 -0.0927 0.3434 1.0000
3.250 0.8648 0.01047 0.00385 -0.0917 0.3379 1.0000
3.500 0.8867 0.01065 0.00400 -0.0906 0.3326 1.0000
3.750 0.9082 0.01086 0.00417 -0.0894 0.3276 1.0000
4.000 0.9310 0.01100 0.00432 -0.0884 0.3230 1.0000
4.250 0.9529 0.01119 0.00449 -0.0873 0.3183 1.0000
4.500 0.9738 0.01146 0.00472 -0.0860 0.3139 1.0000
4.750 0.9968 0.01157 0.00489 -0.0851 0.3093 1.0000
5.000 1.0189 0.01175 0.00506 -0.0841 0.3047 1.0000
5.250 1.0396 0.01198 0.00525 -0.0828 0.2981 1.0000
5.500 1.0622 0.01209 0.00542 -0.0819 0.2925 1.0000
5.750 1.0828 0.01231 0.00560 -0.0806 0.2859 1.0000
6.000 1.1047 0.01247 0.00581 -0.0795 0.2811 1.0000
6.250 1.1258 0.01262 0.00597 -0.0783 0.2729 1.0000
6.500 1.1469 0.01280 0.00618 -0.0772 0.2666 1.0000
6.750 1.1674 0.01298 0.00636 -0.0759 0.2577 1.0000
7.000 1.1882 0.01315 0.00654 -0.0747 0.2456 1.0000
7.250 1.2067 0.01343 0.00675 -0.0731 0.2277 1.0000
7.500 1.2205 0.01406 0.00712 -0.0707 0.1782 1.0000
7.750 1.2057 0.01656 0.00877 -0.0635 0.0453 1.0000
8.000 1.2114 0.01753 0.00965 -0.0595 0.0240 1.0000
8.250 1.2248 0.01801 0.01022 -0.0569 0.0217 1.0000
8.500 1.2363 0.01861 0.01089 -0.0540 0.0200 1.0000
8.750 1.2456 0.01935 0.01171 -0.0508 0.0186 1.0000
9.000 1.2506 0.02033 0.01284 -0.0470 0.0174 1.0000
9.250 1.2599 0.02106 0.01367 -0.0440 0.0167 1.0000
9.500 1.2693 0.02180 0.01449 -0.0412 0.0159 1.0000
9.750 1.2740 0.02281 0.01560 -0.0377 0.0152 1.0000
10.000 1.2807 0.02373 0.01660 -0.0348 0.0146 1.0000
10.250 1.2845 0.02485 0.01782 -0.0316 0.0143 1.0000
10.500 1.2854 0.02620 0.01925 -0.0284 0.0138 1.0000
10.750 1.2803 0.02803 0.02120 -0.0247 0.0134 1.0000
11.000 1.2817 0.02955 0.02282 -0.0221 0.0134 1.0000
11.250 1.2611 0.03280 0.02620 -0.0178 0.0128 1.0000
11.500 1.2601 0.03480 0.02830 -0.0157 0.0128 1.0000
11.750 1.2501 0.03774 0.03135 -0.0132 0.0125 1.0000
12.000 1.2512 0.03985 0.03355 -0.0119 0.0124 1.0000
12.250 1.2527 0.04205 0.03586 -0.0108 0.0121 1.0000
12.500 1.2511 0.04462 0.03852 -0.0096 0.0121 1.0000
12.750 1.2502 0.04722 0.04122 -0.0086 0.0120 1.0000
13.000 1.2507 0.04976 0.04384 -0.0078 0.0119 1.0000
13.250 1.2519 0.05233 0.04654 -0.0074 0.0114 1.0000
13.500 1.2528 0.05496 0.04925 -0.0070 0.0112 1.0000
13.750 1.2537 0.05765 0.05203 -0.0067 0.0109 1.0000
14.000 1.2544 0.06043 0.05488 -0.0066 0.0105 1.0000
14.250 1.2565 0.06295 0.05749 -0.0057 0.0104 1.0000
14.500 1.2591 0.06551 0.06015 -0.0053 0.0104 1.0000
14.750 1.2613 0.06816 0.06289 -0.0047 0.0103 1.0000
15.000 1.2634 0.07088 0.06574 -0.0040 0.0103 1.0000
15.250 1.2638 0.07365 0.06845 -0.0046 0.0095 1.0000
15.500 1.2632 0.07713 0.07224 -0.0039 0.0101 1.0000
15.750 1.2576 0.08142 0.07679 -0.0035 0.0106 1.0000
16.000 1.2545 0.08498 0.08041 -0.0046 0.0101 1.0000
16.250 1.2400 0.09111 0.08689 -0.0044 0.0112 1.0000
16.500 1.2249 0.09714 0.09312 -0.0060 0.0114 1.0000
16.750 1.0187 0.10025 0.09648 0.0002 0.0109 1.0000
17.000 0.9993 0.10379 0.10018 -0.0007 0.0110 1.0000
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Polar data table (+)
Polar graphs
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