GOE 376 AIRFOIL (goe376-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 376 AIRFOIL (goe376-il) Reynolds number: 200,000 Max Cl/Cd: 76.2 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe376-il-200000.txt Download as CSV file: xf-goe376-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 376 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3251 0.10464 0.10113 -0.0234 1.0000 0.0241
-8.250 -0.3302 0.10330 0.09987 -0.0244 1.0000 0.0242
-8.000 -0.3334 0.10151 0.09815 -0.0250 1.0000 0.0242
-7.500 -0.3243 0.09376 0.09048 -0.0235 1.0000 0.0245
-7.250 -0.3186 0.09005 0.08678 -0.0213 1.0000 0.0248
-7.000 -0.3158 0.08716 0.08394 -0.0204 1.0000 0.0252
-6.750 -0.3142 0.08470 0.08153 -0.0201 1.0000 0.0255
-6.500 -0.3135 0.08234 0.07922 -0.0199 1.0000 0.0260
-6.250 -0.3137 0.08018 0.07712 -0.0195 1.0000 0.0263
-6.000 -0.3150 0.07813 0.07511 -0.0189 1.0000 0.0267
-5.750 -0.3165 0.07612 0.07314 -0.0183 1.0000 0.0272
-5.500 -0.3140 0.07392 0.07097 -0.0187 0.9996 0.0278
-5.250 -0.2332 0.06914 0.06585 -0.0407 0.9917 0.0302
-5.000 -0.2106 0.06302 0.05977 -0.0439 0.9864 0.0307
-4.750 -0.1844 0.05887 0.05560 -0.0468 0.9810 0.0315
-4.500 -0.1498 0.05501 0.05166 -0.0520 0.9745 0.0331
-4.250 -0.1088 0.05117 0.04770 -0.0583 0.9681 0.0353
-4.000 -0.0525 0.04696 0.04309 -0.0672 0.9608 0.0385
-3.750 -0.0262 0.04328 0.03945 -0.0696 0.9545 0.0399
-3.500 0.0090 0.04030 0.03636 -0.0731 0.9476 0.0424
-3.250 0.0685 0.03967 0.03507 -0.0783 0.9424 0.0480
-3.000 0.0898 0.03415 0.02976 -0.0807 0.9347 0.0506
-2.750 0.1302 0.03173 0.02719 -0.0843 0.9304 0.0555
-2.500 0.1689 0.02955 0.02462 -0.0863 0.9207 0.0619
-2.250 0.2040 0.02719 0.02225 -0.0890 0.9137 0.0666
-2.000 0.2405 0.02550 0.02022 -0.0905 0.9030 0.0763
-1.500 0.3014 0.02244 0.01692 -0.0922 0.8778 0.0961
-1.250 0.3331 0.02265 0.01667 -0.0921 0.8632 0.1172
-1.000 0.3568 0.02026 0.01438 -0.0921 0.8483 0.1275
-0.750 0.3811 0.01904 0.01304 -0.0917 0.8325 0.1516
-0.500 0.4047 0.01812 0.01205 -0.0910 0.8161 0.1857
0.500 0.5192 0.01561 0.00813 -0.0861 0.7394 0.1171
0.750 0.5449 0.01580 0.00871 -0.0854 0.7210 0.1105
1.000 0.5737 0.01426 0.00628 -0.0836 0.7016 0.0739
1.250 0.5985 0.01343 0.00541 -0.0826 0.6818 0.0701
1.500 0.6231 0.01305 0.00491 -0.0815 0.6621 0.0672
1.750 0.6471 0.01277 0.00456 -0.0803 0.6412 0.0655
2.000 0.6708 0.01257 0.00431 -0.0792 0.6209 0.0650
2.250 0.6945 0.01248 0.00415 -0.0781 0.6015 0.0683
2.500 0.7182 0.01244 0.00403 -0.0771 0.5817 0.0705
2.750 0.7422 0.01246 0.00394 -0.0761 0.5634 0.0714
3.000 0.7664 0.01255 0.00391 -0.0751 0.5463 0.0733
3.250 0.7907 0.01265 0.00392 -0.0742 0.5299 0.0797
3.500 0.8532 0.01130 0.00415 -0.0823 0.5078 1.0000
3.750 0.8768 0.01156 0.00427 -0.0813 0.4914 1.0000
4.000 0.9003 0.01184 0.00442 -0.0803 0.4752 1.0000
4.250 0.9238 0.01213 0.00463 -0.0794 0.4600 1.0000
4.500 0.9472 0.01243 0.00485 -0.0785 0.4453 1.0000
4.750 0.9705 0.01274 0.00509 -0.0775 0.4308 1.0000
5.000 0.9937 0.01305 0.00535 -0.0766 0.4160 1.0000
5.250 1.0165 0.01337 0.00565 -0.0756 0.4004 1.0000
5.500 1.0392 0.01368 0.00594 -0.0746 0.3843 1.0000
5.750 1.0617 0.01400 0.00624 -0.0736 0.3683 1.0000
6.000 1.0840 0.01434 0.00656 -0.0725 0.3525 1.0000
6.250 1.1056 0.01468 0.00687 -0.0714 0.3354 1.0000
6.500 1.1267 0.01500 0.00715 -0.0702 0.3165 1.0000
6.750 1.1478 0.01532 0.00747 -0.0690 0.2970 1.0000
7.000 1.1688 0.01573 0.00785 -0.0678 0.2810 1.0000
7.250 1.1893 0.01616 0.00827 -0.0666 0.2648 1.0000
7.500 1.2091 0.01663 0.00870 -0.0653 0.2480 1.0000
7.750 1.2289 0.01711 0.00917 -0.0640 0.2326 1.0000
8.000 1.2485 0.01760 0.00965 -0.0628 0.2173 1.0000
8.250 1.2686 0.01803 0.01013 -0.0615 0.2002 1.0000
8.500 1.2878 0.01851 0.01064 -0.0602 0.1777 1.0000
8.750 1.3052 0.01917 0.01120 -0.0587 0.1477 1.0000
9.000 1.3175 0.02032 0.01207 -0.0564 0.0994 1.0000
9.250 1.3180 0.02251 0.01375 -0.0527 0.0419 1.0000
9.500 1.3269 0.02387 0.01511 -0.0500 0.0321 1.0000
9.750 1.3367 0.02506 0.01642 -0.0473 0.0292 1.0000
10.000 1.3447 0.02615 0.01767 -0.0443 0.0276 1.0000
10.250 1.3495 0.02736 0.01903 -0.0411 0.0265 1.0000
10.500 1.3526 0.02869 0.02051 -0.0379 0.0258 1.0000
10.750 1.3529 0.03026 0.02221 -0.0346 0.0251 1.0000
11.000 1.3497 0.03218 0.02426 -0.0316 0.0244 1.0000
11.250 1.3465 0.03428 0.02647 -0.0290 0.0240 1.0000
11.500 1.3397 0.03691 0.02920 -0.0267 0.0234 1.0000
11.750 1.3364 0.03948 0.03187 -0.0249 0.0232 1.0000
12.000 1.3336 0.04224 0.03471 -0.0234 0.0228 1.0000
12.250 1.3364 0.04449 0.03713 -0.0224 0.0223 1.0000
12.500 1.3381 0.04700 0.03976 -0.0214 0.0218 1.0000
12.750 1.3409 0.04953 0.04241 -0.0204 0.0217 1.0000
13.000 1.3445 0.05211 0.04512 -0.0193 0.0214 1.0000
13.250 1.3487 0.05475 0.04790 -0.0182 0.0214 1.0000
13.500 1.3512 0.05767 0.05099 -0.0174 0.0212 1.0000
13.750 1.3531 0.06081 0.05431 -0.0167 0.0212 1.0000
14.000 1.3528 0.06422 0.05793 -0.0162 0.0213 1.0000
14.250 1.3492 0.06811 0.06204 -0.0162 0.0214 1.0000
14.500 1.3426 0.07244 0.06660 -0.0165 0.0216 1.0000
14.750 1.3335 0.07715 0.07153 -0.0173 0.0218 1.0000
15.000 1.3224 0.08225 0.07684 -0.0186 0.0220 1.0000
15.250 1.3089 0.08786 0.08266 -0.0204 0.0221 1.0000
15.500 1.2948 0.09378 0.08878 -0.0227 0.0224 1.0000
15.750 1.2794 0.10019 0.09537 -0.0254 0.0225 1.0000
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Polar data table (+)
Polar graphs
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