GOE 391 AIRFOIL (goe391-il) Xfoil prediction polar at RE=200,000 Ncrit=0
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Airfoil: GOE 391 AIRFOIL (goe391-il) Reynolds number: 200,000 Max Cl/Cd: 84.25 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe391-il-200000.txt Download as CSV file: xf-goe391-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 391 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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4568 0.13997 0.13607 -0.0128 1.0000 0.0171
-11.500 -0.4518 0.13687 0.13299 -0.0137 1.0000 0.0175
-11.250 -0.4469 0.13380 0.12993 -0.0145 1.0000 0.0179
-11.000 -0.4422 0.13068 0.12683 -0.0153 1.0000 0.0185
-10.750 -0.4376 0.12763 0.12380 -0.0161 1.0000 0.0191
-10.500 -0.4331 0.12459 0.12078 -0.0169 1.0000 0.0196
-10.250 -0.4287 0.12158 0.11779 -0.0177 1.0000 0.0202
-10.000 -0.4244 0.11866 0.11490 -0.0185 1.0000 0.0208
-9.750 -0.4202 0.11575 0.11198 -0.0192 1.0000 0.0213
-9.500 -0.4164 0.11294 0.10920 -0.0201 1.0000 0.0222
-9.250 -0.4126 0.11029 0.10658 -0.0209 1.0000 0.0226
-9.000 -0.4097 0.10810 0.10443 -0.0221 1.0000 0.0231
-8.750 -0.4080 0.10586 0.10223 -0.0231 1.0000 0.0234
-8.500 -0.4070 0.10358 0.09999 -0.0238 1.0000 0.0235
-8.250 -0.4084 0.10160 0.09807 -0.0245 1.0000 0.0236
-8.000 -0.4135 0.09997 0.09651 -0.0247 1.0000 0.0237
-7.750 -0.4180 0.09788 0.09448 -0.0241 1.0000 0.0238
-7.500 -0.4179 0.09537 0.09201 -0.0247 1.0000 0.0238
-7.250 -0.4171 0.09316 0.08984 -0.0269 1.0000 0.0239
-7.000 -0.4143 0.09042 0.08713 -0.0278 1.0000 0.0240
-6.750 -0.4102 0.08758 0.08429 -0.0288 1.0000 0.0240
-6.500 -0.4050 0.08462 0.08132 -0.0295 1.0000 0.0241
-6.250 -0.3986 0.08166 0.07834 -0.0300 1.0000 0.0241
-6.000 -0.3909 0.07847 0.07513 -0.0307 1.0000 0.0241
-5.500 -0.3892 0.06887 0.06559 -0.0289 1.0000 0.0249
-5.250 -0.3845 0.06556 0.06229 -0.0277 1.0000 0.0254
-5.000 -0.3759 0.06241 0.05912 -0.0275 1.0000 0.0260
-4.750 -0.3644 0.05922 0.05588 -0.0279 1.0000 0.0267
-4.500 -0.3498 0.05603 0.05260 -0.0288 1.0000 0.0275
-4.250 -0.3328 0.05286 0.04934 -0.0298 1.0000 0.0284
-4.000 -0.3131 0.04954 0.04590 -0.0310 1.0000 0.0299
-3.750 -0.2906 0.04637 0.04257 -0.0322 1.0000 0.0317
-3.500 -0.2554 0.04449 0.04026 -0.0336 1.0000 0.0342
-3.250 -0.2311 0.04221 0.03766 -0.0335 1.0000 0.0345
-3.000 -0.2120 0.03640 0.03195 -0.0360 0.9984 0.0372
-2.750 -0.1743 0.03370 0.02898 -0.0388 0.9955 0.0423
-2.500 -0.1361 0.03042 0.02522 -0.0410 0.9924 0.0475
-2.250 -0.1024 0.02827 0.02290 -0.0430 0.9892 0.0554
-2.000 -0.0642 0.02680 0.02088 -0.0449 0.9859 0.0735
-1.750 -0.0349 0.02426 0.01835 -0.0465 0.9825 0.0907
-1.250 0.0438 0.01976 0.01280 -0.0482 0.9779 0.0678
-1.000 0.0778 0.01820 0.01068 -0.0480 0.9735 0.0595
-0.750 0.1146 0.01693 0.00936 -0.0500 0.9696 0.0671
-0.500 0.1525 0.01624 0.00852 -0.0518 0.9650 0.0696
-0.250 0.1890 0.01568 0.00787 -0.0534 0.9588 0.0712
0.000 0.2315 0.01498 0.00719 -0.0563 0.9551 0.0702
0.250 0.2613 0.01452 0.00674 -0.0567 0.9471 0.0705
0.500 0.3025 0.01411 0.00633 -0.0594 0.9426 0.0725
0.750 0.3351 0.01373 0.00597 -0.0602 0.9349 0.0841
1.000 0.3979 0.01138 0.00580 -0.0678 0.9351 1.0000
1.250 0.4453 0.01115 0.00550 -0.0716 0.9293 1.0000
1.500 0.4834 0.01093 0.00527 -0.0734 0.9203 1.0000
1.750 0.5323 0.01056 0.00493 -0.0774 0.9152 1.0000
2.000 0.5639 0.01039 0.00479 -0.0779 0.9051 1.0000
2.250 0.6012 0.01002 0.00446 -0.0792 0.8939 1.0000
2.500 0.6388 0.00944 0.00393 -0.0800 0.8748 1.0000
2.750 0.6690 0.00906 0.00356 -0.0794 0.8481 1.0000
3.000 0.6980 0.00888 0.00337 -0.0789 0.8190 1.0000
3.250 0.7238 0.00884 0.00335 -0.0779 0.7846 1.0000
3.500 0.7490 0.00889 0.00328 -0.0766 0.7299 1.0000
3.750 0.7701 0.00924 0.00325 -0.0745 0.6440 1.0000
4.000 0.7875 0.00982 0.00347 -0.0721 0.5649 1.0000
4.250 0.8015 0.01060 0.00381 -0.0692 0.4572 1.0000
4.500 0.8117 0.01178 0.00431 -0.0659 0.3262 1.0000
4.750 0.8205 0.01353 0.00507 -0.0628 0.1442 1.0000
5.000 0.8367 0.01481 0.00594 -0.0608 0.0809 1.0000
5.250 0.8570 0.01557 0.00678 -0.0593 0.0735 1.0000
5.500 0.8764 0.01642 0.00774 -0.0577 0.0673 1.0000
5.750 0.8973 0.01712 0.00852 -0.0565 0.0597 1.0000
6.000 0.9162 0.01819 0.00967 -0.0549 0.0515 1.0000
6.250 0.9335 0.01986 0.01135 -0.0530 0.0411 1.0000
6.500 0.9530 0.02262 0.01405 -0.0516 0.0335 1.0000
6.750 0.9756 0.02359 0.01526 -0.0503 0.0279 1.0000
7.000 0.9982 0.02599 0.01780 -0.0494 0.0249 1.0000
7.500 1.0381 0.03225 0.02491 -0.0460 0.0221 1.0000
7.750 1.0542 0.03503 0.02818 -0.0436 0.0210 1.0000
8.000 1.0653 0.03893 0.03258 -0.0408 0.0212 1.0000
8.250 1.0712 0.04334 0.03745 -0.0377 0.0218 1.0000
8.500 1.0170 0.04009 0.03541 -0.0276 0.0307 1.0000
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Polar data table (+)
Polar graphs
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