GOE 488 AIRFOIL (goe488-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 488 AIRFOIL (goe488-il) Reynolds number: 500,000 Max Cl/Cd: 79.69 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe488-il-500000-n5.txt Download as CSV file: xf-goe488-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 488 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4508 0.08662 0.08434 -0.0275 1.0000 0.0126
-8.750 -0.4563 0.08307 0.08083 -0.0282 1.0000 0.0129
-8.500 -0.4672 0.07971 0.07752 -0.0282 1.0000 0.0133
-8.250 -0.4846 0.07673 0.07460 -0.0272 1.0000 0.0136
-8.000 -0.4947 0.06014 0.05794 -0.0460 0.9931 0.0155
-7.750 -0.4700 0.05800 0.05575 -0.0495 0.9899 0.0159
-7.500 -0.4435 0.05614 0.05384 -0.0528 0.9874 0.0165
-7.250 -0.4193 0.05262 0.05024 -0.0572 0.9836 0.0174
-7.000 -0.4128 0.02741 0.02388 -0.0713 0.9733 0.0220
-6.750 -0.3902 0.02395 0.02006 -0.0728 0.9698 0.0232
-6.500 -0.3595 0.02350 0.01955 -0.0740 0.9681 0.0238
-6.250 -0.3321 0.02277 0.01871 -0.0745 0.9646 0.0246
-6.000 -0.3049 0.02180 0.01759 -0.0750 0.9609 0.0255
-5.750 -0.2768 0.02007 0.01558 -0.0757 0.9579 0.0264
-5.500 -0.2503 0.01867 0.01393 -0.0759 0.9525 0.0274
-5.250 -0.2215 0.01746 0.01250 -0.0764 0.9473 0.0284
-5.000 -0.1943 0.01632 0.01112 -0.0764 0.9406 0.0290
-4.750 -0.1655 0.01534 0.00995 -0.0767 0.9347 0.0294
-4.500 -0.1389 0.01450 0.00893 -0.0765 0.9279 0.0297
-4.250 -0.1108 0.01373 0.00800 -0.0766 0.9219 0.0299
-4.000 -0.0843 0.01306 0.00720 -0.0763 0.9140 0.0301
-3.750 -0.0563 0.01243 0.00643 -0.0762 0.9068 0.0303
-3.500 -0.0301 0.01198 0.00588 -0.0758 0.8990 0.0306
-3.250 -0.0024 0.01158 0.00540 -0.0757 0.8923 0.0308
-3.000 0.0236 0.01106 0.00480 -0.0752 0.8844 0.0309
-2.750 0.0505 0.01058 0.00421 -0.0749 0.8771 0.0309
-2.500 0.0765 0.01016 0.00374 -0.0744 0.8689 0.0310
-2.250 0.1032 0.00981 0.00333 -0.0740 0.8619 0.0311
-2.000 0.1293 0.00952 0.00298 -0.0735 0.8531 0.0312
-1.750 0.1551 0.00915 0.00257 -0.0730 0.8441 0.0317
-1.500 0.1808 0.00879 0.00213 -0.0724 0.8339 0.0330
-1.250 0.2067 0.00857 0.00187 -0.0718 0.8230 0.0349
-1.000 0.2329 0.00843 0.00171 -0.0713 0.8107 0.0365
-0.750 0.2590 0.00833 0.00157 -0.0707 0.7965 0.0381
-0.500 0.2851 0.00826 0.00145 -0.0702 0.7818 0.0397
-0.250 0.3110 0.00821 0.00135 -0.0696 0.7646 0.0414
0.000 0.3366 0.00819 0.00126 -0.0690 0.7416 0.0431
0.250 0.3611 0.00818 0.00117 -0.0681 0.7068 0.0509
0.500 0.3837 0.00825 0.00113 -0.0669 0.6602 0.0765
0.750 0.4050 0.00827 0.00119 -0.0655 0.6136 0.1588
1.000 0.4268 0.00843 0.00128 -0.0643 0.5600 0.2133
1.250 0.4470 0.00872 0.00140 -0.0629 0.4801 0.2684
1.500 0.4577 0.00794 0.00153 -0.0599 0.4114 0.7031
1.750 0.5065 0.00789 0.00183 -0.0643 0.3516 0.9769
2.000 0.5571 0.00816 0.00194 -0.0695 0.3271 0.9983
2.250 0.5848 0.00832 0.00202 -0.0695 0.3160 1.0000
2.500 0.6085 0.00845 0.00211 -0.0686 0.3071 1.0000
2.750 0.6319 0.00860 0.00221 -0.0677 0.2976 1.0000
3.000 0.6554 0.00875 0.00232 -0.0667 0.2878 1.0000
3.250 0.6793 0.00889 0.00242 -0.0659 0.2782 1.0000
3.500 0.7030 0.00904 0.00255 -0.0650 0.2695 1.0000
3.750 0.7268 0.00920 0.00268 -0.0641 0.2584 1.0000
4.000 0.7499 0.00941 0.00281 -0.0632 0.2378 1.0000
4.250 0.7722 0.00971 0.00298 -0.0621 0.2065 1.0000
4.500 0.7932 0.01014 0.00320 -0.0609 0.1680 1.0000
5.000 0.8355 0.01107 0.00379 -0.0585 0.1050 1.0000
5.250 0.8551 0.01173 0.00420 -0.0571 0.0595 1.0000
5.500 0.8776 0.01211 0.00454 -0.0561 0.0476 1.0000
5.750 0.8990 0.01263 0.00493 -0.0550 0.0221 1.0000
6.000 0.9214 0.01306 0.00531 -0.0539 0.0161 1.0000
6.250 0.9446 0.01340 0.00571 -0.0530 0.0139 1.0000
6.500 0.9674 0.01378 0.00618 -0.0521 0.0124 1.0000
6.750 0.9896 0.01423 0.00669 -0.0511 0.0113 1.0000
7.000 1.0112 0.01477 0.00731 -0.0499 0.0103 1.0000
7.250 1.0310 0.01551 0.00815 -0.0485 0.0094 1.0000
7.500 1.0527 0.01599 0.00871 -0.0474 0.0090 1.0000
7.750 1.0740 0.01650 0.00929 -0.0464 0.0084 1.0000
8.000 1.0947 0.01705 0.00991 -0.0452 0.0079 1.0000
8.250 1.1145 0.01768 0.01061 -0.0439 0.0074 1.0000
8.500 1.1335 0.01837 0.01135 -0.0425 0.0070 1.0000
8.750 1.1513 0.01914 0.01219 -0.0410 0.0067 1.0000
9.000 1.1657 0.02019 0.01333 -0.0389 0.0064 1.0000
9.250 1.1780 0.02140 0.01463 -0.0366 0.0062 1.0000
9.500 1.1934 0.02228 0.01563 -0.0347 0.0061 1.0000
9.750 1.2075 0.02323 0.01670 -0.0327 0.0059 1.0000
10.000 1.2201 0.02425 0.01783 -0.0305 0.0057 1.0000
10.250 1.2303 0.02529 0.01897 -0.0278 0.0055 1.0000
10.500 1.2397 0.02630 0.02010 -0.0252 0.0053 1.0000
10.750 1.2489 0.02732 0.02122 -0.0227 0.0051 1.0000
11.000 1.2571 0.02842 0.02243 -0.0202 0.0049 1.0000
11.250 1.2642 0.02961 0.02372 -0.0177 0.0048 1.0000
11.500 1.2706 0.03084 0.02506 -0.0154 0.0046 1.0000
11.750 1.2761 0.03215 0.02647 -0.0132 0.0045 1.0000
12.000 1.2782 0.03388 0.02835 -0.0108 0.0044 1.0000
12.250 1.2799 0.03563 0.03021 -0.0088 0.0043 1.0000
12.500 1.2787 0.03783 0.03255 -0.0069 0.0043 1.0000
12.750 1.2778 0.04002 0.03487 -0.0054 0.0042 1.0000
13.000 1.2724 0.04288 0.03789 -0.0040 0.0042 1.0000
13.250 1.2640 0.04630 0.04148 -0.0031 0.0041 1.0000
13.500 1.2531 0.05026 0.04563 -0.0029 0.0040 1.0000
13.750 1.2454 0.05410 0.04963 -0.0034 0.0041 1.0000
14.000 1.2354 0.05864 0.05435 -0.0047 0.0040 1.0000
14.250 1.2237 0.06381 0.05970 -0.0066 0.0040 1.0000
14.500 1.2113 0.06954 0.06561 -0.0094 0.0040 1.0000
14.750 1.1995 0.07563 0.07187 -0.0127 0.0040 1.0000
15.000 1.1854 0.08252 0.07893 -0.0167 0.0040 1.0000
15.250 1.1689 0.09023 0.08681 -0.0211 0.0040 1.0000
15.500 1.1534 0.09777 0.09448 -0.0254 0.0040 1.0000
15.750 1.1358 0.10603 0.10288 -0.0301 0.0040 1.0000
16.000 1.1195 0.11417 0.11114 -0.0348 0.0040 1.0000
16.250 1.1037 0.12256 0.11966 -0.0396 0.0040 1.0000
16.500 1.0876 0.13117 0.12837 -0.0445 0.0041 1.0000
16.750 1.0703 0.14095 0.13828 -0.0502 0.0040 1.0000
17.250 1.0401 0.16010 0.15762 -0.0609 0.0041 1.0000
17.500 1.0209 0.17218 0.16983 -0.0675 0.0042 1.0000
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