Fage & Collins 2 (fg2-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: Fage & Collins 2 (fg2-il) Reynolds number: 100,000 Max Cl/Cd: 51.41 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fg2-il-100000.txt Download as CSV file: xf-fg2-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4144 0.10321 0.09831 -0.0219 1.0000 0.0596
-8.500 -0.4215 0.10108 0.09626 -0.0238 1.0000 0.0599
-8.250 -0.4313 0.09905 0.09432 -0.0257 1.0000 0.0602
-8.000 -0.4371 0.09674 0.09201 -0.0298 1.0000 0.0605
-7.750 -0.4176 0.08993 0.08528 -0.0213 1.0000 0.0639
-7.500 -0.4166 0.08702 0.08239 -0.0208 1.0000 0.0657
-7.250 -0.4163 0.08392 0.07934 -0.0213 1.0000 0.0684
-7.000 -0.4161 0.08090 0.07635 -0.0228 1.0000 0.0708
-6.750 -0.4163 0.07843 0.07380 -0.0279 1.0000 0.0737
-6.500 -0.4161 0.07620 0.07137 -0.0307 1.0000 0.0748
-6.250 -0.4097 0.07048 0.06592 -0.0259 1.0000 0.0774
-6.000 -0.4036 0.06764 0.06311 -0.0244 1.0000 0.0807
-5.750 -0.3955 0.06501 0.06032 -0.0261 1.0000 0.0873
-5.500 -0.3901 0.06136 0.05654 -0.0264 1.0000 0.0905
-5.250 -0.3835 0.05843 0.05375 -0.0236 1.0000 0.0954
-5.000 -0.3740 0.05579 0.05081 -0.0243 1.0000 0.1052
-4.750 -0.3663 0.05296 0.04813 -0.0218 1.0000 0.1120
-4.500 -0.3567 0.05017 0.04519 -0.0211 1.0000 0.1221
-4.250 -0.3460 0.04798 0.04278 -0.0201 1.0000 0.1352
-4.000 -0.3356 0.04582 0.04051 -0.0186 1.0000 0.1497
-3.750 -0.3259 0.04331 0.03800 -0.0167 1.0000 0.1654
-3.500 -0.3157 0.04114 0.03585 -0.0148 1.0000 0.1821
-3.250 -0.3069 0.03931 0.03400 -0.0127 1.0000 0.2109
-3.000 -0.2993 0.03756 0.03234 -0.0100 1.0000 0.2430
-2.750 -0.2940 0.03601 0.03087 -0.0069 1.0000 0.2862
-2.500 -0.2884 0.03462 0.02956 -0.0036 1.0000 0.3291
-2.250 -0.2623 0.03248 0.02763 -0.0031 0.9921 0.3955
-2.000 -0.2275 0.03001 0.02531 -0.0032 0.9790 0.4704
-1.750 -0.0998 0.02677 0.01865 -0.0191 0.9699 0.1325
-1.500 -0.0486 0.02424 0.01569 -0.0222 0.9605 0.1080
-1.250 0.0006 0.02281 0.01390 -0.0252 0.9480 0.0998
-1.000 0.0486 0.02144 0.01236 -0.0285 0.9352 0.0999
-0.750 0.0967 0.02008 0.01090 -0.0316 0.9223 0.0968
-0.500 0.1442 0.01887 0.00968 -0.0347 0.9092 0.0958
-0.250 0.1904 0.01776 0.00863 -0.0376 0.8961 0.0968
0.000 0.2392 0.01683 0.00766 -0.0409 0.8821 0.1016
0.250 0.2922 0.01597 0.00677 -0.0453 0.8659 0.1140
0.500 0.4465 0.01296 0.00597 -0.0715 0.8545 1.0000
0.750 0.4964 0.01276 0.00548 -0.0753 0.8210 1.0000
1.000 0.5364 0.01274 0.00521 -0.0773 0.7841 1.0000
1.250 0.5711 0.01285 0.00505 -0.0782 0.7495 1.0000
1.500 0.6013 0.01309 0.00503 -0.0782 0.7184 1.0000
1.750 0.6280 0.01342 0.00513 -0.0777 0.6897 1.0000
2.000 0.6527 0.01380 0.00533 -0.0768 0.6631 1.0000
2.250 0.6770 0.01422 0.00557 -0.0759 0.6394 1.0000
2.500 0.7009 0.01465 0.00585 -0.0749 0.6178 1.0000
2.750 0.7250 0.01509 0.00615 -0.0740 0.5989 1.0000
3.000 0.7469 0.01550 0.00651 -0.0727 0.5793 1.0000
3.250 0.7690 0.01587 0.00681 -0.0714 0.5608 1.0000
3.500 0.7914 0.01624 0.00708 -0.0702 0.5437 1.0000
3.750 0.8136 0.01658 0.00736 -0.0689 0.5273 1.0000
4.000 0.8358 0.01693 0.00770 -0.0677 0.5123 1.0000
4.250 0.8580 0.01729 0.00809 -0.0665 0.4988 1.0000
4.500 0.8803 0.01768 0.00852 -0.0654 0.4862 1.0000
4.750 0.9027 0.01807 0.00897 -0.0643 0.4742 1.0000
5.000 0.9254 0.01846 0.00944 -0.0633 0.4626 1.0000
5.250 0.9480 0.01884 0.00984 -0.0622 0.4506 1.0000
5.500 0.9704 0.01920 0.01023 -0.0610 0.4379 1.0000
5.750 0.9917 0.01954 0.01064 -0.0596 0.4238 1.0000
6.000 1.0124 0.01991 0.01111 -0.0582 0.4089 1.0000
6.250 1.0310 0.02024 0.01156 -0.0563 0.3908 1.0000
6.500 1.0485 0.02047 0.01181 -0.0541 0.3696 1.0000
6.750 1.0645 0.02073 0.01208 -0.0517 0.3464 1.0000
7.000 1.0811 0.02108 0.01244 -0.0495 0.3245 1.0000
7.250 1.0959 0.02142 0.01291 -0.0471 0.3014 1.0000
7.500 1.1107 0.02172 0.01325 -0.0446 0.2796 1.0000
7.750 1.1232 0.02185 0.01351 -0.0418 0.2519 1.0000
8.000 1.1363 0.02211 0.01384 -0.0392 0.2173 1.0000
8.250 1.1458 0.02292 0.01447 -0.0362 0.1723 1.0000
8.500 1.1465 0.02486 0.01598 -0.0321 0.1050 1.0000
8.750 1.1471 0.02689 0.01760 -0.0280 0.0666 1.0000
9.000 1.1492 0.02859 0.01932 -0.0241 0.0577 1.0000
9.250 1.1484 0.03034 0.02109 -0.0199 0.0536 1.0000
9.500 1.1483 0.03188 0.02275 -0.0156 0.0511 1.0000
9.750 1.1501 0.03342 0.02442 -0.0118 0.0489 1.0000
10.000 1.1536 0.03509 0.02618 -0.0085 0.0471 1.0000
10.250 1.1585 0.03688 0.02802 -0.0057 0.0450 1.0000
10.500 1.1666 0.03924 0.03033 -0.0036 0.0428 1.0000
10.750 1.1788 0.04158 0.03283 -0.0019 0.0409 1.0000
11.000 1.1939 0.04399 0.03549 -0.0005 0.0402 1.0000
11.250 1.2051 0.04672 0.03849 0.0012 0.0395 1.0000
11.500 1.2125 0.04962 0.04167 0.0030 0.0395 1.0000
11.750 1.2129 0.05278 0.04514 0.0052 0.0394 1.0000
12.000 1.2078 0.05607 0.04873 0.0075 0.0395 1.0000
12.250 1.1990 0.05957 0.05252 0.0093 0.0397 1.0000
12.500 1.1863 0.06337 0.05660 0.0107 0.0400 1.0000
12.750 1.1722 0.06744 0.06091 0.0112 0.0403 1.0000
13.000 1.1549 0.07205 0.06575 0.0110 0.0405 1.0000
13.250 1.1355 0.07718 0.07111 0.0097 0.0407 1.0000
13.500 1.1155 0.08287 0.07700 0.0077 0.0409 1.0000
13.750 1.0951 0.08909 0.08339 0.0049 0.0412 1.0000
14.000 1.0729 0.09590 0.09036 0.0014 0.0415 1.0000
14.250 1.0532 0.10298 0.09755 -0.0022 0.0418 1.0000
14.500 1.0297 0.11104 0.10577 -0.0069 0.0421 1.0000
14.750 0.9974 0.12152 0.11644 -0.0152 0.0430 1.0000
15.000 0.9034 0.15524 0.15006 -0.0358 0.0498 1.0000
15.250 0.9001 0.16164 0.15643 -0.0382 0.0512 1.0000
15.500 0.9033 0.16589 0.16068 -0.0389 0.0524 1.0000
15.750 0.8921 0.17870 0.17342 -0.0443 0.0634 1.0000
16.000 0.6593 0.17247 0.16756 -0.0374 0.1077 1.0000
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Polar data table (+)
Polar graphs
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