GOE 335 (D.F.W.) AIRFOIL (goe335-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 335 (D.F.W.) AIRFOIL (goe335-il) Reynolds number: 200,000 Max Cl/Cd: 75.44 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe335-il-200000-n5.txt Download as CSV file: xf-goe335-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 335 (D.F.W.) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.3052 0.08950 0.08631 -0.0235 1.0000 0.0214
-7.000 -0.3109 0.08765 0.08453 -0.0220 1.0000 0.0213
-6.750 -0.3143 0.08546 0.08242 -0.0215 1.0000 0.0217
-6.500 -0.2883 0.07856 0.07550 -0.0328 0.9923 0.0153
-6.250 -0.2636 0.07378 0.07070 -0.0388 0.9860 0.0149
-6.000 -0.2331 0.06850 0.06538 -0.0474 0.9776 0.0150
-5.250 -0.1293 0.05192 0.04849 -0.0717 0.9431 0.0159
-4.750 -0.0616 0.04085 0.03706 -0.0837 0.9145 0.0166
-4.500 -0.0307 0.03968 0.03579 -0.0862 0.9000 0.0185
-4.250 0.0069 0.03580 0.03166 -0.0906 0.8859 0.0205
-4.000 0.0452 0.03045 0.02588 -0.0948 0.8722 0.0217
-3.750 0.0822 0.02472 0.01946 -0.0972 0.8589 0.0250
-3.500 0.1121 0.02117 0.01534 -0.0985 0.8454 0.0273
-3.250 0.1408 0.02029 0.01423 -0.0990 0.8314 0.0299
-3.000 0.1690 0.01886 0.01238 -0.0990 0.8177 0.0336
-2.750 0.1969 0.01728 0.01030 -0.0987 0.8052 0.0357
-2.500 0.2245 0.01664 0.00929 -0.0984 0.7940 0.0383
-2.250 0.2510 0.01516 0.00747 -0.0981 0.7838 0.0398
-2.000 0.2775 0.01442 0.00654 -0.0977 0.7729 0.0411
-1.750 0.3040 0.01385 0.00583 -0.0973 0.7620 0.0422
-1.500 0.3305 0.01351 0.00538 -0.0969 0.7514 0.0448
-1.250 0.3569 0.01309 0.00483 -0.0964 0.7407 0.0459
-1.000 0.3830 0.01265 0.00429 -0.0959 0.7286 0.0458
-0.750 0.4089 0.01229 0.00385 -0.0953 0.7157 0.0460
-0.500 0.4348 0.01201 0.00349 -0.0948 0.7018 0.0463
-0.250 0.4606 0.01179 0.00318 -0.0942 0.6870 0.0469
0.000 0.4864 0.01163 0.00293 -0.0936 0.6715 0.0480
0.250 0.5122 0.01153 0.00271 -0.0930 0.6547 0.0497
0.500 0.5379 0.01145 0.00254 -0.0924 0.6353 0.0529
1.000 0.5877 0.01124 0.00240 -0.0911 0.5878 0.1394
1.250 0.6103 0.01082 0.00248 -0.0903 0.5596 0.3724
1.500 0.6448 0.00977 0.00249 -0.0916 0.5260 1.0000
1.750 0.6686 0.01003 0.00252 -0.0907 0.4971 1.0000
2.000 0.6927 0.01030 0.00261 -0.0899 0.4738 1.0000
2.250 0.7169 0.01058 0.00272 -0.0892 0.4558 1.0000
2.500 0.7414 0.01084 0.00285 -0.0885 0.4413 1.0000
2.750 0.7662 0.01110 0.00301 -0.0879 0.4291 1.0000
3.000 0.7911 0.01136 0.00320 -0.0874 0.4191 1.0000
3.250 0.8159 0.01163 0.00339 -0.0868 0.4101 1.0000
3.500 0.8413 0.01187 0.00360 -0.0864 0.4017 1.0000
3.750 0.8661 0.01215 0.00384 -0.0858 0.3943 1.0000
4.000 0.8915 0.01238 0.00407 -0.0854 0.3863 1.0000
4.250 0.9163 0.01266 0.00432 -0.0849 0.3792 1.0000
4.500 0.9417 0.01289 0.00460 -0.0845 0.3719 1.0000
4.750 0.9664 0.01317 0.00488 -0.0839 0.3644 1.0000
5.000 0.9914 0.01340 0.00516 -0.0834 0.3558 1.0000
5.250 1.0161 0.01368 0.00546 -0.0829 0.3489 1.0000
5.500 1.0412 0.01392 0.00580 -0.0825 0.3420 1.0000
5.750 1.0654 0.01419 0.00611 -0.0819 0.3325 1.0000
6.000 1.0881 0.01445 0.00634 -0.0810 0.3097 1.0000
6.250 1.1112 0.01473 0.00663 -0.0803 0.2888 1.0000
6.500 1.1337 0.01508 0.00698 -0.0795 0.2587 1.0000
6.750 1.1515 0.01587 0.00743 -0.0781 0.1908 1.0000
7.000 1.1582 0.01804 0.00880 -0.0755 0.0772 1.0000
7.250 1.1700 0.01962 0.01008 -0.0733 0.0228 1.0000
7.500 1.1880 0.02051 0.01105 -0.0717 0.0180 1.0000
7.750 1.2046 0.02151 0.01225 -0.0700 0.0148 1.0000
8.000 1.2203 0.02253 0.01347 -0.0681 0.0137 1.0000
8.250 1.2350 0.02353 0.01471 -0.0662 0.0131 1.0000
8.500 1.2479 0.02462 0.01596 -0.0641 0.0121 1.0000
8.750 1.2585 0.02578 0.01726 -0.0618 0.0110 1.0000
9.000 1.2653 0.02702 0.01862 -0.0590 0.0103 1.0000
9.250 1.2685 0.02844 0.02017 -0.0557 0.0099 1.0000
9.500 1.2696 0.03007 0.02191 -0.0525 0.0096 1.0000
9.750 1.2692 0.03194 0.02388 -0.0495 0.0093 1.0000
10.000 1.2686 0.03401 0.02606 -0.0469 0.0091 1.0000
10.250 1.2666 0.03652 0.02866 -0.0444 0.0088 1.0000
10.500 1.2681 0.03916 0.03140 -0.0423 0.0086 1.0000
10.750 1.2750 0.04121 0.03358 -0.0408 0.0084 1.0000
11.000 1.2817 0.04319 0.03572 -0.0395 0.0082 1.0000
11.250 1.2877 0.04525 0.03802 -0.0384 0.0078 1.0000
11.500 1.2923 0.04749 0.04042 -0.0374 0.0073 1.0000
11.750 1.2960 0.05001 0.04311 -0.0365 0.0070 1.0000
12.000 1.2986 0.05282 0.04611 -0.0357 0.0069 1.0000
12.250 1.2997 0.05589 0.04937 -0.0350 0.0068 1.0000
12.500 1.2989 0.05919 0.05288 -0.0346 0.0066 1.0000
12.750 1.2961 0.06277 0.05665 -0.0345 0.0065 1.0000
13.000 1.2914 0.06671 0.06081 -0.0347 0.0065 1.0000
13.250 1.2847 0.07100 0.06531 -0.0353 0.0064 1.0000
13.500 1.2763 0.07567 0.07019 -0.0364 0.0064 1.0000
13.750 1.2667 0.08066 0.07539 -0.0379 0.0063 1.0000
14.000 1.2551 0.08618 0.08113 -0.0400 0.0064 1.0000
14.250 1.2427 0.09214 0.08731 -0.0426 0.0064 1.0000
14.500 1.2296 0.09852 0.09390 -0.0457 0.0064 1.0000
14.750 1.2155 0.10543 0.10102 -0.0494 0.0064 1.0000
15.000 1.2011 0.11280 0.10859 -0.0536 0.0064 1.0000
15.250 1.1861 0.12063 0.11661 -0.0582 0.0065 1.0000
15.500 1.1708 0.12888 0.12503 -0.0633 0.0065 1.0000
15.750 1.1554 0.13761 0.13393 -0.0687 0.0066 1.0000
16.000 1.1400 0.14687 0.14334 -0.0746 0.0067 1.0000
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Polar data table (+)
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