GOE 399 AIRFOIL (goe399-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 399 AIRFOIL (goe399-il) Reynolds number: 100,000 Max Cl/Cd: 60.35 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe399-il-100000-n5.txt Download as CSV file: xf-goe399-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 399 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3438 0.10062 0.09579 -0.0304 1.0000 0.0390
-8.000 -0.3478 0.09870 0.09397 -0.0311 1.0000 0.0392
-7.750 -0.3513 0.09664 0.09200 -0.0322 1.0000 0.0393
-7.500 -0.3498 0.09396 0.08939 -0.0340 1.0000 0.0394
-7.250 -0.3471 0.09109 0.08657 -0.0355 1.0000 0.0395
-7.000 -0.3440 0.08811 0.08363 -0.0369 1.0000 0.0395
-6.750 -0.3405 0.08500 0.08056 -0.0379 1.0000 0.0396
-6.500 -0.3370 0.08182 0.07740 -0.0384 1.0000 0.0396
-6.250 -0.3335 0.07866 0.07427 -0.0385 1.0000 0.0396
-5.750 -0.3307 0.07140 0.06714 -0.0321 0.9976 0.0355
-5.500 -0.2967 0.06486 0.06047 -0.0416 0.9895 0.0316
-5.250 -0.2635 0.06018 0.05566 -0.0485 0.9820 0.0336
-5.000 -0.2269 0.05500 0.05031 -0.0561 0.9747 0.0351
-4.750 -0.1903 0.04949 0.04457 -0.0628 0.9672 0.0346
-4.500 -0.1547 0.04427 0.03906 -0.0683 0.9592 0.0348
-4.250 -0.1125 0.03841 0.03266 -0.0741 0.9533 0.0382
-4.000 -0.0782 0.03337 0.02694 -0.0768 0.9450 0.0396
-3.750 -0.0461 0.03117 0.02465 -0.0795 0.9396 0.0429
-3.500 -0.0149 0.02887 0.02194 -0.0808 0.9311 0.0475
-3.250 0.0220 0.02571 0.01809 -0.0826 0.9249 0.0501
-3.000 0.0525 0.02392 0.01588 -0.0833 0.9143 0.0545
-2.750 0.0849 0.02227 0.01389 -0.0841 0.9040 0.0562
-2.500 0.1194 0.02079 0.01204 -0.0851 0.8949 0.0583
-2.250 0.1501 0.01964 0.01058 -0.0853 0.8841 0.0606
-2.000 0.1804 0.01898 0.00959 -0.0854 0.8741 0.0652
-1.750 0.2114 0.01799 0.00851 -0.0859 0.8657 0.0682
-1.500 0.2412 0.01723 0.00766 -0.0860 0.8561 0.0700
-1.250 0.2696 0.01661 0.00696 -0.0859 0.8457 0.0726
-1.000 0.2986 0.01605 0.00633 -0.0858 0.8361 0.0764
-0.750 0.3277 0.01552 0.00572 -0.0857 0.8267 0.0817
-0.500 0.3549 0.01515 0.00532 -0.0854 0.8154 0.0910
-0.250 0.3831 0.01482 0.00496 -0.0852 0.8047 0.1063
0.000 0.4121 0.01446 0.00473 -0.0853 0.7944 0.1450
0.500 0.4906 0.01228 0.00440 -0.0899 0.7731 1.0000
0.750 0.5171 0.01238 0.00432 -0.0893 0.7611 1.0000
1.000 0.5436 0.01249 0.00428 -0.0888 0.7492 1.0000
1.250 0.5700 0.01261 0.00428 -0.0882 0.7372 1.0000
1.500 0.5962 0.01273 0.00428 -0.0877 0.7249 1.0000
1.750 0.6218 0.01287 0.00434 -0.0870 0.7115 1.0000
2.000 0.6472 0.01302 0.00442 -0.0863 0.6977 1.0000
2.250 0.6725 0.01318 0.00452 -0.0856 0.6831 1.0000
2.500 0.6976 0.01333 0.00461 -0.0848 0.6674 1.0000
2.750 0.7221 0.01349 0.00473 -0.0840 0.6495 1.0000
3.000 0.7467 0.01366 0.00489 -0.0831 0.6315 1.0000
3.250 0.7713 0.01385 0.00504 -0.0823 0.6144 1.0000
3.500 0.7961 0.01405 0.00523 -0.0816 0.5981 1.0000
3.750 0.8208 0.01426 0.00546 -0.0808 0.5822 1.0000
4.000 0.8454 0.01450 0.00569 -0.0801 0.5666 1.0000
4.250 0.8698 0.01475 0.00596 -0.0793 0.5499 1.0000
4.500 0.8935 0.01501 0.00623 -0.0784 0.5304 1.0000
4.750 0.9166 0.01530 0.00650 -0.0773 0.5090 1.0000
5.000 0.9394 0.01562 0.00681 -0.0763 0.4867 1.0000
5.250 0.9626 0.01597 0.00718 -0.0753 0.4689 1.0000
5.500 0.9861 0.01634 0.00760 -0.0745 0.4538 1.0000
5.750 1.0083 0.01675 0.00806 -0.0734 0.4334 1.0000
6.000 1.0291 0.01720 0.00850 -0.0721 0.4076 1.0000
6.250 1.0503 0.01763 0.00901 -0.0709 0.3821 1.0000
6.500 1.0717 0.01806 0.00957 -0.0697 0.3591 1.0000
6.750 1.0909 0.01858 0.01016 -0.0682 0.3213 1.0000
7.000 1.1031 0.01964 0.01081 -0.0659 0.2387 1.0000
7.250 1.1049 0.02204 0.01220 -0.0628 0.1098 1.0000
7.500 1.1162 0.02363 0.01360 -0.0606 0.0769 1.0000
7.750 1.1281 0.02505 0.01500 -0.0585 0.0603 1.0000
8.000 1.1384 0.02653 0.01658 -0.0561 0.0468 1.0000
8.250 1.1478 0.02798 0.01814 -0.0536 0.0371 1.0000
8.500 1.1552 0.02951 0.01977 -0.0509 0.0325 1.0000
8.750 1.1630 0.03088 0.02128 -0.0482 0.0288 1.0000
9.000 1.1682 0.03231 0.02277 -0.0455 0.0259 1.0000
9.250 1.1737 0.03390 0.02455 -0.0427 0.0240 1.0000
9.500 1.1796 0.03571 0.02650 -0.0401 0.0226 1.0000
9.750 1.1881 0.03765 0.02858 -0.0379 0.0213 1.0000
10.000 1.1980 0.03956 0.03062 -0.0360 0.0201 1.0000
10.250 1.2063 0.04149 0.03266 -0.0343 0.0187 1.0000
10.500 1.2140 0.04425 0.03555 -0.0327 0.0172 1.0000
10.750 1.2253 0.04717 0.03872 -0.0313 0.0166 1.0000
11.000 1.2329 0.05017 0.04204 -0.0296 0.0163 1.0000
11.250 1.2356 0.05334 0.04554 -0.0279 0.0160 1.0000
11.500 1.2334 0.05681 0.04934 -0.0263 0.0158 1.0000
11.750 1.2277 0.06040 0.05324 -0.0249 0.0157 1.0000
12.000 1.2181 0.06439 0.05753 -0.0240 0.0156 1.0000
12.250 1.2063 0.06866 0.06209 -0.0237 0.0156 1.0000
12.500 1.1924 0.07334 0.06703 -0.0241 0.0155 1.0000
12.750 1.1764 0.07852 0.07247 -0.0252 0.0155 1.0000
13.000 1.1600 0.08405 0.07823 -0.0270 0.0155 1.0000
13.250 1.1424 0.09015 0.08454 -0.0296 0.0156 1.0000
13.500 1.1241 0.09683 0.09141 -0.0330 0.0157 1.0000
13.750 1.1046 0.10429 0.09906 -0.0372 0.0158 1.0000
14.000 1.0864 0.11209 0.10700 -0.0420 0.0160 1.0000
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Polar data table (+)
Polar graphs
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