GOE 704 AIRFOIL (goe704-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 704 AIRFOIL (goe704-il) Reynolds number: 200,000 Max Cl/Cd: 57.86 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe704-il-200000.txt Download as CSV file: xf-goe704-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 704 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.9086 0.05684 0.05240 -0.0513 1.0000 0.0316
-12.750 -0.9313 0.05225 0.04754 -0.0515 1.0000 0.0316
-12.500 -0.9496 0.04845 0.04352 -0.0499 1.0000 0.0317
-12.250 -0.9611 0.04537 0.04027 -0.0474 1.0000 0.0320
-12.000 -0.9636 0.04319 0.03800 -0.0448 1.0000 0.0326
-11.750 -0.9621 0.04147 0.03620 -0.0423 1.0000 0.0333
-11.500 -0.9586 0.03966 0.03422 -0.0400 1.0000 0.0343
-11.250 -0.9542 0.03766 0.03199 -0.0377 1.0000 0.0353
-11.000 -0.9488 0.03556 0.02958 -0.0352 1.0000 0.0364
-10.750 -0.9408 0.03363 0.02728 -0.0328 1.0000 0.0374
-10.500 -0.9308 0.03111 0.02455 -0.0309 1.0000 0.0386
-10.250 -0.9147 0.02966 0.02308 -0.0295 1.0000 0.0401
-10.000 -0.8981 0.02844 0.02175 -0.0281 1.0000 0.0421
-9.750 -0.8813 0.02728 0.02035 -0.0264 1.0000 0.0446
-9.500 -0.8655 0.02563 0.01865 -0.0249 1.0000 0.0472
-9.250 -0.8476 0.02474 0.01774 -0.0235 1.0000 0.0503
-9.000 -0.8305 0.02383 0.01657 -0.0216 1.0000 0.0537
-8.750 -0.8177 0.02272 0.01560 -0.0194 1.0000 0.0579
-8.500 -0.8072 0.02226 0.01502 -0.0164 1.0000 0.0625
-8.250 -0.8046 0.02167 0.01447 -0.0124 1.0000 0.0663
-8.000 -0.7754 0.02126 0.01391 -0.0132 0.9960 0.0738
-7.750 -0.7365 0.02077 0.01345 -0.0160 0.9902 0.0832
-7.500 -0.6966 0.02040 0.01307 -0.0189 0.9846 0.0927
-7.250 -0.6572 0.02004 0.01264 -0.0216 0.9789 0.1024
-7.000 -0.6183 0.01982 0.01225 -0.0241 0.9727 0.1127
-6.750 -0.5807 0.01963 0.01208 -0.0265 0.9664 0.1221
-6.500 -0.5457 0.01915 0.01155 -0.0282 0.9586 0.1308
-6.250 -0.5121 0.01897 0.01120 -0.0294 0.9507 0.1394
-6.000 -0.4804 0.01836 0.01063 -0.0303 0.9425 0.1470
-5.750 -0.4519 0.01816 0.01028 -0.0304 0.9333 0.1544
-5.500 -0.4233 0.01757 0.00970 -0.0306 0.9253 0.1611
-5.250 -0.3974 0.01733 0.00939 -0.0301 0.9160 0.1679
-5.000 -0.3708 0.01689 0.00888 -0.0297 0.9087 0.1741
-4.750 -0.3453 0.01659 0.00859 -0.0293 0.8998 0.1804
-4.500 -0.3194 0.01640 0.00825 -0.0286 0.8929 0.1867
-4.250 -0.2934 0.01594 0.00789 -0.0283 0.8850 0.1933
-4.000 -0.2676 0.01571 0.00760 -0.0277 0.8782 0.2003
-3.750 -0.2417 0.01537 0.00729 -0.0273 0.8713 0.2074
-3.500 -0.2157 0.01515 0.00705 -0.0268 0.8643 0.2153
-3.250 -0.1903 0.01484 0.00677 -0.0262 0.8585 0.2233
-3.000 -0.1639 0.01467 0.00659 -0.0259 0.8510 0.2340
-2.750 -0.1390 0.01438 0.00637 -0.0252 0.8451 0.2467
-2.500 -0.1135 0.01413 0.00622 -0.0247 0.8381 0.2633
-2.250 -0.0891 0.01382 0.00603 -0.0239 0.8312 0.2877
-2.000 -0.0657 0.01346 0.00586 -0.0229 0.8242 0.3287
-1.750 -0.0444 0.01295 0.00567 -0.0215 0.8153 0.3966
-1.500 -0.0279 0.01215 0.00546 -0.0191 0.8072 0.5244
-1.250 0.0235 0.01195 0.00654 -0.0212 0.7997 0.9015
-1.000 0.0666 0.01253 0.00700 -0.0230 0.7936 0.9328
-0.750 0.1158 0.01302 0.00741 -0.0266 0.7857 0.9549
-0.500 0.1810 0.01335 0.00758 -0.0335 0.7793 0.9719
-0.250 0.2407 0.01341 0.00758 -0.0399 0.7705 0.9855
0.000 0.3007 0.01326 0.00730 -0.0464 0.7628 0.9974
0.250 0.3350 0.01317 0.00718 -0.0479 0.7527 1.0000
0.500 0.3597 0.01311 0.00703 -0.0472 0.7434 1.0000
0.750 0.3846 0.01302 0.00688 -0.0465 0.7326 1.0000
1.000 0.4098 0.01296 0.00677 -0.0460 0.7214 1.0000
1.250 0.4348 0.01290 0.00664 -0.0453 0.7117 1.0000
1.500 0.4602 0.01283 0.00654 -0.0448 0.7007 1.0000
1.750 0.4856 0.01278 0.00647 -0.0443 0.6895 1.0000
2.000 0.5108 0.01272 0.00636 -0.0437 0.6783 1.0000
2.250 0.5360 0.01265 0.00624 -0.0430 0.6663 1.0000
2.500 0.5612 0.01259 0.00618 -0.0425 0.6522 1.0000
2.750 0.5864 0.01254 0.00612 -0.0419 0.6375 1.0000
3.000 0.6115 0.01249 0.00604 -0.0413 0.6213 1.0000
3.250 0.6365 0.01246 0.00596 -0.0407 0.6031 1.0000
3.500 0.6613 0.01245 0.00593 -0.0401 0.5800 1.0000
3.750 0.6856 0.01250 0.00587 -0.0393 0.5530 1.0000
4.000 0.7096 0.01262 0.00586 -0.0386 0.5207 1.0000
4.250 0.7331 0.01284 0.00592 -0.0378 0.4860 1.0000
4.500 0.7562 0.01315 0.00605 -0.0371 0.4533 1.0000
4.750 0.7791 0.01350 0.00624 -0.0363 0.4250 1.0000
5.000 0.8016 0.01389 0.00649 -0.0355 0.4011 1.0000
5.250 0.8242 0.01426 0.00677 -0.0347 0.3806 1.0000
5.500 0.8465 0.01463 0.00707 -0.0339 0.3631 1.0000
5.750 0.8684 0.01502 0.00739 -0.0330 0.3478 1.0000
6.000 0.8899 0.01542 0.00774 -0.0320 0.3344 1.0000
6.500 0.9321 0.01619 0.00845 -0.0299 0.3099 1.0000
6.750 0.9529 0.01657 0.00884 -0.0288 0.2993 1.0000
7.000 0.9730 0.01701 0.00921 -0.0276 0.2899 1.0000
7.250 0.9935 0.01733 0.00962 -0.0264 0.2810 1.0000
7.500 1.0132 0.01778 0.01003 -0.0251 0.2732 1.0000
7.750 1.0328 0.01812 0.01046 -0.0238 0.2653 1.0000
8.000 1.0516 0.01856 0.01088 -0.0223 0.2576 1.0000
8.250 1.0694 0.01888 0.01126 -0.0207 0.2485 1.0000
8.500 1.0864 0.01925 0.01168 -0.0189 0.2395 1.0000
8.750 1.1021 0.01966 0.01206 -0.0170 0.2304 1.0000
9.000 1.1178 0.01996 0.01249 -0.0150 0.2211 1.0000
9.250 1.1318 0.02040 0.01293 -0.0128 0.2124 1.0000
9.500 1.1450 0.02075 0.01335 -0.0105 0.2027 1.0000
9.750 1.1575 0.02115 0.01382 -0.0080 0.1929 1.0000
10.000 1.1674 0.02163 0.01431 -0.0053 0.1834 1.0000
10.250 1.1774 0.02206 0.01481 -0.0025 0.1731 1.0000
10.500 1.1864 0.02254 0.01535 0.0004 0.1621 1.0000
10.750 1.1915 0.02307 0.01591 0.0039 0.1514 1.0000
11.000 1.1963 0.02369 0.01655 0.0072 0.1402 1.0000
11.250 1.2038 0.02441 0.01730 0.0097 0.1253 1.0000
11.500 1.2076 0.02552 0.01833 0.0123 0.1049 1.0000
11.750 1.2051 0.02727 0.01994 0.0150 0.0853 1.0000
12.000 1.1997 0.02951 0.02209 0.0176 0.0667 1.0000
12.250 1.1992 0.03158 0.02409 0.0194 0.0505 1.0000
12.500 1.1985 0.03376 0.02626 0.0209 0.0441 1.0000
12.750 1.1947 0.03632 0.02882 0.0222 0.0407 1.0000
13.000 1.1941 0.03872 0.03134 0.0231 0.0385 1.0000
13.250 1.1917 0.04138 0.03410 0.0238 0.0368 1.0000
13.500 1.1866 0.04442 0.03722 0.0243 0.0354 1.0000
13.750 1.1780 0.04792 0.04077 0.0245 0.0343 1.0000
14.000 1.1733 0.05114 0.04411 0.0247 0.0334 1.0000
14.250 1.1704 0.05425 0.04736 0.0246 0.0324 1.0000
14.500 1.1668 0.05756 0.05077 0.0244 0.0315 1.0000
14.750 1.1631 0.06100 0.05430 0.0240 0.0307 1.0000
15.000 1.1591 0.06454 0.05792 0.0234 0.0299 1.0000
15.250 1.1554 0.06807 0.06150 0.0229 0.0293 1.0000
15.500 1.1533 0.07132 0.06478 0.0227 0.0287 1.0000
15.750 1.1544 0.07384 0.06729 0.0234 0.0280 1.0000
16.000 1.1550 0.07702 0.07060 0.0229 0.0277 1.0000
16.250 1.1556 0.08023 0.07394 0.0224 0.0273 1.0000
16.500 1.1559 0.08351 0.07735 0.0219 0.0269 1.0000
16.750 1.1552 0.08698 0.08096 0.0211 0.0265 1.0000
17.000 1.1537 0.09065 0.08477 0.0202 0.0262 1.0000
17.250 1.1512 0.09455 0.08879 0.0190 0.0258 1.0000
17.500 1.1480 0.09864 0.09301 0.0176 0.0254 1.0000
17.750 1.1433 0.10305 0.09755 0.0159 0.0250 1.0000
18.000 1.1379 0.10764 0.10227 0.0140 0.0247 1.0000
18.250 1.1323 0.11235 0.10710 0.0119 0.0244 1.0000
18.500 1.1264 0.11717 0.11204 0.0096 0.0241 1.0000
18.750 1.1182 0.12256 0.11757 0.0069 0.0239 1.0000
19.000 1.1057 0.12904 0.12423 0.0033 0.0239 1.0000
19.250 1.0884 0.13681 0.13221 -0.0014 0.0240 1.0000
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