GOE 573 AIRFOIL (goe573-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 573 AIRFOIL (goe573-il) Reynolds number: 500,000 Max Cl/Cd: 100.04 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe573-il-500000-n5.txt Download as CSV file: xf-goe573-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 573 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 0.0248 0.08797 0.08401 -0.1142 0.6673 0.0122
-10.250 0.0283 0.08489 0.08088 -0.1154 0.6547 0.0125
-10.000 0.0181 0.07906 0.07505 -0.1177 0.6487 0.0137
-9.750 0.0216 0.07634 0.07230 -0.1188 0.6387 0.0139
-9.500 0.0282 0.07430 0.07022 -0.1196 0.6290 0.0141
-9.250 0.0374 0.07277 0.06866 -0.1201 0.6204 0.0145
-9.000 0.0384 0.06989 0.06576 -0.1211 0.6130 0.0146
-8.750 0.0396 0.06724 0.06311 -0.1220 0.6065 0.0150
-8.500 0.0343 0.06395 0.05983 -0.1233 0.6002 0.0152
-8.000 0.0099 0.05737 0.05326 -0.1235 0.5897 0.0160
-7.750 -0.0209 0.04935 0.04516 -0.1247 0.5873 0.0173
-7.500 -0.0159 0.04698 0.04271 -0.1241 0.5809 0.0175
-7.250 -0.0069 0.04507 0.04072 -0.1234 0.5747 0.0178
-6.750 -0.0434 0.02918 0.02402 -0.1157 0.5687 0.0212
-6.500 -0.0280 0.02836 0.02307 -0.1140 0.5618 0.0214
-6.250 -0.0102 0.02764 0.02224 -0.1127 0.5546 0.0217
-6.000 0.0077 0.02701 0.02148 -0.1112 0.5469 0.0221
-5.750 0.0231 0.02565 0.01995 -0.1094 0.5403 0.0227
-5.500 0.0358 0.02365 0.01768 -0.1068 0.5338 0.0236
-5.250 0.0424 0.02023 0.01368 -0.1029 0.5291 0.0253
-5.000 0.0597 0.01885 0.01195 -0.1008 0.5230 0.0259
-4.750 0.0776 0.01769 0.01055 -0.0990 0.5166 0.0266
-4.500 0.0995 0.01719 0.00995 -0.0979 0.5107 0.0270
-4.250 0.1217 0.01678 0.00943 -0.0969 0.5043 0.0275
-4.000 0.1438 0.01625 0.00876 -0.0957 0.4986 0.0279
-3.750 0.1669 0.01575 0.00813 -0.0947 0.4930 0.0284
-3.500 0.1899 0.01527 0.00751 -0.0937 0.4873 0.0288
-3.250 0.2131 0.01484 0.00695 -0.0928 0.4822 0.0294
-3.000 0.2371 0.01447 0.00648 -0.0919 0.4765 0.0301
-2.750 0.2608 0.01418 0.00609 -0.0910 0.4715 0.0308
-2.500 0.2845 0.01385 0.00566 -0.0902 0.4671 0.0312
-2.250 0.3089 0.01358 0.00531 -0.0894 0.4632 0.0316
-2.000 0.3328 0.01332 0.00499 -0.0886 0.4591 0.0319
-1.750 0.3563 0.01312 0.00471 -0.0877 0.4553 0.0321
-1.500 0.3789 0.01278 0.00432 -0.0866 0.4520 0.0327
-1.250 0.4021 0.01250 0.00403 -0.0856 0.4490 0.0334
-1.000 0.4254 0.01234 0.00384 -0.0847 0.4458 0.0341
-0.750 0.4487 0.01224 0.00373 -0.0838 0.4427 0.0350
-0.500 0.4717 0.01216 0.00362 -0.0828 0.4399 0.0358
0.000 0.5178 0.01200 0.00340 -0.0808 0.4346 0.0375
0.250 0.5413 0.01193 0.00332 -0.0800 0.4318 0.0385
0.500 0.5647 0.01189 0.00326 -0.0790 0.4291 0.0394
0.750 0.5878 0.01186 0.00321 -0.0781 0.4268 0.0405
1.000 0.6104 0.01183 0.00316 -0.0770 0.4245 0.0428
1.250 0.6331 0.01184 0.00315 -0.0760 0.4223 0.0454
1.500 0.6563 0.01186 0.00316 -0.0751 0.4204 0.0495
1.750 0.6796 0.01183 0.00318 -0.0743 0.4187 0.0589
2.000 0.7019 0.01175 0.00324 -0.0732 0.4168 0.1071
2.250 0.7221 0.01158 0.00331 -0.0718 0.4147 0.2061
2.500 0.7131 0.01032 0.00343 -0.0643 0.4133 0.7294
2.750 1.0007 0.01117 0.00453 -0.1221 0.4071 1.0000
3.000 1.0222 0.01132 0.00464 -0.1210 0.4055 1.0000
3.250 1.0445 0.01140 0.00474 -0.1200 0.4038 1.0000
3.500 1.0666 0.01150 0.00484 -0.1189 0.4018 1.0000
3.750 1.0882 0.01160 0.00495 -0.1178 0.3992 1.0000
4.000 1.1092 0.01172 0.00506 -0.1166 0.3967 1.0000
4.250 1.1296 0.01185 0.00517 -0.1153 0.3941 1.0000
4.500 1.1490 0.01202 0.00530 -0.1137 0.3910 1.0000
4.750 1.1695 0.01215 0.00545 -0.1124 0.3889 1.0000
5.000 1.1903 0.01225 0.00558 -0.1112 0.3863 1.0000
5.250 1.2107 0.01237 0.00572 -0.1099 0.3844 1.0000
5.500 1.2306 0.01251 0.00589 -0.1085 0.3826 1.0000
5.750 1.2500 0.01265 0.00605 -0.1070 0.3808 1.0000
6.000 1.2687 0.01280 0.00621 -0.1053 0.3789 1.0000
6.250 1.2869 0.01297 0.00640 -0.1036 0.3771 1.0000
6.500 1.3041 0.01315 0.00658 -0.1017 0.3754 1.0000
6.750 1.3209 0.01329 0.00677 -0.0997 0.3738 1.0000
7.000 1.3373 0.01340 0.00694 -0.0976 0.3717 1.0000
7.250 1.3506 0.01350 0.00708 -0.0949 0.3667 1.0000
7.500 1.3634 0.01366 0.00725 -0.0921 0.3629 1.0000
7.750 1.3758 0.01384 0.00744 -0.0893 0.3586 1.0000
8.000 1.3911 0.01397 0.00763 -0.0871 0.3537 1.0000
8.250 1.4041 0.01417 0.00786 -0.0845 0.3487 1.0000
8.500 1.4167 0.01440 0.00810 -0.0818 0.3434 1.0000
8.750 1.4308 0.01461 0.00835 -0.0795 0.3363 1.0000
9.000 1.4418 0.01491 0.00866 -0.0767 0.3296 1.0000
9.250 1.4530 0.01524 0.00900 -0.0740 0.3188 1.0000
9.500 1.4593 0.01574 0.00947 -0.0705 0.3031 1.0000
9.750 1.4623 0.01643 0.01009 -0.0667 0.2841 1.0000
10.000 1.4602 0.01741 0.01097 -0.0623 0.2630 1.0000
10.250 1.4537 0.01871 0.01216 -0.0576 0.2407 1.0000
10.500 1.4446 0.02033 0.01367 -0.0530 0.2189 1.0000
10.750 1.4370 0.02207 0.01535 -0.0491 0.2006 1.0000
11.000 1.4199 0.02463 0.01779 -0.0448 0.1715 1.0000
11.250 1.3928 0.02829 0.02128 -0.0405 0.1340 1.0000
11.500 1.3633 0.03267 0.02555 -0.0371 0.1033 1.0000
11.750 1.3325 0.03765 0.03046 -0.0345 0.0723 1.0000
12.000 1.3127 0.04191 0.03470 -0.0329 0.0533 1.0000
12.250 1.2829 0.04740 0.04015 -0.0313 0.0282 1.0000
12.500 1.2725 0.05105 0.04384 -0.0305 0.0213 1.0000
12.750 1.2664 0.05435 0.04719 -0.0299 0.0183 1.0000
13.000 1.2642 0.05726 0.05018 -0.0294 0.0174 1.0000
13.250 1.2592 0.06054 0.05354 -0.0290 0.0160 1.0000
13.500 1.2546 0.06387 0.05695 -0.0287 0.0150 1.0000
13.750 1.2518 0.06702 0.06018 -0.0285 0.0142 1.0000
14.000 1.2493 0.07017 0.06342 -0.0283 0.0138 1.0000
14.250 1.2476 0.07325 0.06658 -0.0282 0.0131 1.0000
14.500 1.2445 0.07655 0.06995 -0.0282 0.0125 1.0000
14.750 1.2405 0.08002 0.07350 -0.0282 0.0120 1.0000
15.000 1.2363 0.08352 0.07706 -0.0283 0.0115 1.0000
15.250 1.2301 0.08734 0.08096 -0.0285 0.0110 1.0000
15.500 1.2278 0.09068 0.08439 -0.0287 0.0108 1.0000
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