GOE 416A AIRFOIL (goe416a-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 416A AIRFOIL (goe416a-il) Reynolds number: 100,000 Max Cl/Cd: 46.45 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe416a-il-100000.txt Download as CSV file: xf-goe416a-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 416A 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4393 0.11453 0.10995 -0.0062 1.0000 0.1597
-10.500 -0.4673 0.11115 0.10665 -0.0099 1.0000 0.1679
-10.250 -0.6068 0.11445 0.10977 -0.0016 1.0000 0.1553
-10.000 -0.5782 0.11200 0.10727 0.0025 1.0000 0.1655
-9.750 -0.5720 0.10830 0.10357 0.0025 1.0000 0.1736
-9.500 -0.5819 0.10423 0.09959 -0.0003 1.0000 0.1842
-9.250 -0.6113 0.10060 0.09610 -0.0065 1.0000 0.1960
-9.000 -0.5876 0.09790 0.09336 -0.0030 1.0000 0.2095
-7.000 -0.6287 0.03725 0.02948 -0.0391 1.0000 0.0726
-6.750 -0.6070 0.03367 0.02567 -0.0382 1.0000 0.0684
-6.500 -0.5826 0.03174 0.02302 -0.0366 1.0000 0.0626
-6.250 -0.5577 0.02957 0.02069 -0.0355 1.0000 0.0598
-6.000 -0.5336 0.02716 0.01817 -0.0343 1.0000 0.0573
-5.750 -0.5093 0.02531 0.01620 -0.0330 1.0000 0.0554
-5.500 -0.4857 0.02377 0.01460 -0.0315 1.0000 0.0543
-5.250 -0.4634 0.02243 0.01329 -0.0301 1.0000 0.0541
-5.000 -0.4426 0.02126 0.01218 -0.0286 1.0000 0.0550
-4.750 -0.4223 0.02030 0.01121 -0.0273 1.0000 0.0582
-4.500 -0.4014 0.01947 0.01031 -0.0261 1.0000 0.0608
-4.250 -0.3802 0.01846 0.00920 -0.0252 1.0000 0.0634
-4.000 -0.3576 0.01762 0.00824 -0.0246 1.0000 0.0688
-3.750 -0.3339 0.01678 0.00738 -0.0241 1.0000 0.0827
-3.500 -0.3136 0.01486 0.00737 -0.0243 1.0000 0.4762
-3.250 -0.2948 0.01588 0.00843 -0.0215 1.0000 0.5392
-3.000 -0.2768 0.01667 0.00925 -0.0187 1.0000 0.5786
-2.750 -0.2602 0.01723 0.00993 -0.0156 1.0000 0.6088
-2.500 -0.2421 0.01749 0.01023 -0.0134 1.0000 0.6283
-2.250 -0.2275 0.01790 0.01075 -0.0101 1.0000 0.6564
-2.000 -0.2092 0.01805 0.01091 -0.0084 1.0000 0.6745
-1.750 -0.1863 0.01802 0.01081 -0.0084 1.0000 0.6834
-1.500 -0.1499 0.01803 0.01070 -0.0112 0.9950 0.6920
-1.250 -0.0990 0.01795 0.01053 -0.0165 0.9837 0.6982
-1.000 -0.0498 0.01785 0.01035 -0.0214 0.9715 0.7044
-0.750 -0.0015 0.01771 0.01013 -0.0262 0.9589 0.7100
-0.500 0.0451 0.01755 0.00996 -0.0302 0.9464 0.7152
-0.250 0.0934 0.01736 0.00973 -0.0346 0.9343 0.7209
0.000 0.1372 0.01713 0.00951 -0.0378 0.9212 0.7259
0.250 0.1772 0.01689 0.00929 -0.0399 0.9064 0.7313
0.500 0.2144 0.01663 0.00902 -0.0415 0.8894 0.7369
0.750 0.2465 0.01634 0.00877 -0.0416 0.8717 0.7420
1.000 0.2771 0.01607 0.00851 -0.0414 0.8540 0.7481
1.250 0.3040 0.01589 0.00835 -0.0407 0.8329 0.7538
1.500 0.3305 0.01567 0.00815 -0.0397 0.8131 0.7599
1.750 0.3570 0.01551 0.00797 -0.0389 0.7924 0.7672
2.000 0.3821 0.01535 0.00783 -0.0377 0.7706 0.7744
2.250 0.4086 0.01525 0.00774 -0.0369 0.7506 0.7824
2.500 0.4346 0.01523 0.00776 -0.0362 0.7301 0.7913
2.750 0.4608 0.01521 0.00776 -0.0355 0.7112 0.8016
3.000 0.4868 0.01524 0.00782 -0.0348 0.6918 0.8138
3.250 0.5123 0.01527 0.00796 -0.0340 0.6719 0.8284
3.500 0.5374 0.01530 0.00806 -0.0331 0.6535 0.8469
3.750 0.5622 0.01531 0.00820 -0.0320 0.6355 0.8754
4.000 0.5954 0.01529 0.00842 -0.0328 0.6136 0.9400
4.250 0.6318 0.01549 0.00856 -0.0350 0.5896 1.0000
4.500 0.6615 0.01573 0.00869 -0.0356 0.5643 1.0000
4.750 0.6892 0.01593 0.00883 -0.0356 0.5361 1.0000
5.000 0.7159 0.01618 0.00906 -0.0353 0.5078 1.0000
5.250 0.7420 0.01650 0.00930 -0.0349 0.4787 1.0000
5.500 0.7667 0.01687 0.00958 -0.0342 0.4455 1.0000
5.750 0.7908 0.01728 0.00992 -0.0335 0.4111 1.0000
6.000 0.8148 0.01772 0.01034 -0.0329 0.3788 1.0000
6.250 0.8385 0.01812 0.01074 -0.0322 0.3450 1.0000
6.500 0.8612 0.01854 0.01114 -0.0314 0.3063 1.0000
6.750 0.8814 0.01932 0.01175 -0.0304 0.2583 1.0000
7.000 0.8976 0.02081 0.01294 -0.0290 0.1980 1.0000
7.250 0.9146 0.02220 0.01402 -0.0277 0.1410 1.0000
7.500 0.9295 0.02414 0.01559 -0.0262 0.1102 1.0000
7.750 0.9467 0.02604 0.01744 -0.0248 0.0887 1.0000
8.000 0.9655 0.02810 0.01945 -0.0235 0.0755 1.0000
8.250 0.9855 0.03013 0.02153 -0.0224 0.0658 1.0000
8.500 1.0077 0.03298 0.02424 -0.0218 0.0596 1.0000
8.750 1.0293 0.03532 0.02703 -0.0205 0.0561 1.0000
9.000 1.0483 0.03752 0.02944 -0.0195 0.0518 1.0000
9.250 1.0666 0.04140 0.03335 -0.0190 0.0486 1.0000
9.500 1.0785 0.04501 0.03744 -0.0174 0.0478 1.0000
9.750 1.0862 0.04859 0.04153 -0.0155 0.0474 1.0000
10.000 1.0892 0.05261 0.04602 -0.0136 0.0473 1.0000
10.250 1.0876 0.05689 0.05070 -0.0117 0.0474 1.0000
10.500 1.0810 0.06114 0.05531 -0.0098 0.0475 1.0000
10.750 1.0696 0.06535 0.05983 -0.0081 0.0476 1.0000
11.000 1.0532 0.06939 0.06410 -0.0062 0.0478 1.0000
11.250 1.0363 0.07403 0.06892 -0.0056 0.0480 1.0000
11.750 0.9419 0.08967 0.08537 -0.0166 0.0525 1.0000
12.000 0.8938 0.10421 0.10002 -0.0282 0.0549 1.0000
12.250 0.8675 0.11637 0.11211 -0.0356 0.0574 1.0000
12.500 0.8616 0.12302 0.11873 -0.0378 0.0589 1.0000
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