GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il) Reynolds number: 200,000 Max Cl/Cd: 74.48 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe188-il-200000-n5.txt Download as CSV file: xf-goe188-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 188 (SCHTTE-LANZ 3U10) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3163 0.09139 0.08820 -0.0256 1.0000 0.0124
-7.250 -0.3155 0.08884 0.08572 -0.0268 1.0000 0.0126
-7.000 -0.3121 0.08607 0.08302 -0.0289 1.0000 0.0127
-6.750 -0.2961 0.08240 0.07937 -0.0348 0.9923 0.0130
-6.500 -0.2671 0.07791 0.07482 -0.0435 0.9722 0.0132
-6.250 -0.2380 0.07351 0.07035 -0.0507 0.9494 0.0134
-6.000 -0.2079 0.06910 0.06583 -0.0571 0.9287 0.0135
-5.750 -0.1786 0.06485 0.06144 -0.0624 0.9099 0.0136
-5.500 -0.1519 0.06094 0.05736 -0.0664 0.8917 0.0137
-5.250 -0.1271 0.05731 0.05354 -0.0692 0.8750 0.0137
-5.000 -0.1035 0.05392 0.04994 -0.0712 0.8603 0.0137
-4.750 -0.0800 0.05070 0.04651 -0.0727 0.8476 0.0138
-4.500 -0.0626 0.04467 0.04030 -0.0748 0.8368 0.0144
-4.250 -0.0425 0.04095 0.03641 -0.0758 0.8255 0.0150
-4.000 -0.0205 0.03803 0.03328 -0.0765 0.8131 0.0156
-3.750 0.0029 0.03545 0.03048 -0.0771 0.7995 0.0165
-3.500 0.0278 0.03311 0.02789 -0.0775 0.7857 0.0183
-3.250 0.0549 0.03088 0.02536 -0.0777 0.7728 0.0206
-3.000 0.0844 0.02900 0.02313 -0.0775 0.7618 0.0232
-2.750 0.1171 0.02908 0.02266 -0.0766 0.7526 0.0251
-2.500 0.1413 0.02473 0.01815 -0.0774 0.7441 0.0271
-2.250 0.1682 0.02300 0.01622 -0.0776 0.7356 0.0299
-1.750 0.2276 0.01988 0.01245 -0.0766 0.7187 0.0218
-1.500 0.2574 0.01824 0.01046 -0.0760 0.7109 0.0169
-1.250 0.2872 0.01743 0.00933 -0.0753 0.7020 0.0146
-1.000 0.3152 0.01613 0.00783 -0.0751 0.6939 0.0157
-0.750 0.3430 0.01523 0.00680 -0.0749 0.6850 0.0173
-0.500 0.3710 0.01442 0.00586 -0.0745 0.6760 0.0169
-0.250 0.3985 0.01373 0.00507 -0.0741 0.6675 0.0171
0.000 0.4261 0.01315 0.00445 -0.0739 0.6582 0.0178
0.250 0.4537 0.01277 0.00399 -0.0738 0.6487 0.0212
0.500 0.4815 0.01250 0.00354 -0.0737 0.6389 0.0231
0.750 0.5094 0.01233 0.00322 -0.0736 0.6280 0.0257
1.000 0.5373 0.01218 0.00297 -0.0735 0.6174 0.0368
1.500 0.5885 0.00999 0.00286 -0.0725 0.5953 1.0000
1.750 0.6156 0.01011 0.00283 -0.0724 0.5817 1.0000
2.000 0.6427 0.01024 0.00283 -0.0723 0.5670 1.0000
2.250 0.6697 0.01037 0.00286 -0.0722 0.5514 1.0000
2.500 0.6966 0.01051 0.00291 -0.0721 0.5344 1.0000
2.750 0.7232 0.01068 0.00297 -0.0719 0.5153 1.0000
3.000 0.7494 0.01089 0.00305 -0.0717 0.4951 1.0000
3.250 0.7755 0.01112 0.00315 -0.0715 0.4747 1.0000
3.500 0.8014 0.01138 0.00331 -0.0712 0.4560 1.0000
3.750 0.8271 0.01167 0.00348 -0.0710 0.4391 1.0000
4.000 0.8528 0.01197 0.00369 -0.0708 0.4239 1.0000
4.250 0.8787 0.01225 0.00393 -0.0706 0.4108 1.0000
4.500 0.9046 0.01253 0.00418 -0.0704 0.3995 1.0000
4.750 0.9305 0.01282 0.00445 -0.0703 0.3902 1.0000
5.000 0.9565 0.01310 0.00475 -0.0702 0.3815 1.0000
5.250 0.9826 0.01338 0.00506 -0.0700 0.3739 1.0000
5.500 1.0084 0.01367 0.00538 -0.0699 0.3663 1.0000
5.750 1.0343 0.01396 0.00574 -0.0697 0.3592 1.0000
6.000 1.0598 0.01427 0.00610 -0.0695 0.3517 1.0000
6.250 1.0851 0.01457 0.00647 -0.0693 0.3412 1.0000
6.500 1.1098 0.01490 0.00686 -0.0690 0.3282 1.0000
6.750 1.1342 0.01524 0.00724 -0.0687 0.3148 1.0000
7.000 1.1586 0.01559 0.00766 -0.0683 0.3029 1.0000
7.250 1.1828 0.01595 0.00810 -0.0680 0.2920 1.0000
7.500 1.2073 0.01629 0.00857 -0.0676 0.2807 1.0000
7.750 1.2309 0.01667 0.00909 -0.0671 0.2664 1.0000
8.000 1.2516 0.01724 0.00959 -0.0664 0.2327 1.0000
8.250 1.2662 0.01839 0.01038 -0.0649 0.1734 1.0000
8.500 1.2786 0.01983 0.01149 -0.0632 0.1131 1.0000
8.750 1.2837 0.02193 0.01310 -0.0607 0.0549 1.0000
9.000 1.2924 0.02357 0.01453 -0.0584 0.0177 1.0000
9.250 1.3017 0.02506 0.01602 -0.0560 0.0105 1.0000
9.500 1.3122 0.02631 0.01753 -0.0539 0.0087 1.0000
9.750 1.3173 0.02771 0.01914 -0.0510 0.0078 1.0000
10.000 1.3174 0.02947 0.02111 -0.0477 0.0072 1.0000
10.250 1.3205 0.03115 0.02298 -0.0453 0.0069 1.0000
10.500 1.3225 0.03304 0.02507 -0.0432 0.0064 1.0000
10.750 1.3232 0.03521 0.02741 -0.0415 0.0059 1.0000
11.000 1.3223 0.03770 0.03006 -0.0403 0.0055 1.0000
11.250 1.3187 0.04064 0.03315 -0.0393 0.0052 1.0000
11.500 1.3115 0.04413 0.03680 -0.0387 0.0050 1.0000
11.750 1.3049 0.04773 0.04055 -0.0382 0.0049 1.0000
12.000 1.3013 0.05111 0.04409 -0.0380 0.0048 1.0000
12.250 1.2968 0.05470 0.04784 -0.0379 0.0047 1.0000
12.500 1.2919 0.05839 0.05170 -0.0379 0.0046 1.0000
12.750 1.2868 0.06217 0.05563 -0.0380 0.0045 1.0000
13.000 1.2817 0.06601 0.05962 -0.0382 0.0044 1.0000
13.250 1.2766 0.06989 0.06365 -0.0383 0.0043 1.0000
13.500 1.2718 0.07384 0.06776 -0.0386 0.0043 1.0000
13.750 1.2672 0.07789 0.07196 -0.0391 0.0042 1.0000
14.000 1.2623 0.08207 0.07631 -0.0396 0.0041 1.0000
14.250 1.2571 0.08644 0.08085 -0.0404 0.0041 1.0000
14.500 1.2514 0.09104 0.08563 -0.0414 0.0040 1.0000
14.750 1.2449 0.09590 0.09067 -0.0427 0.0040 1.0000
15.000 1.2377 0.10103 0.09597 -0.0444 0.0039 1.0000
15.250 1.2299 0.10643 0.10155 -0.0465 0.0039 1.0000
15.500 1.2217 0.11206 0.10735 -0.0488 0.0038 1.0000
15.750 1.2132 0.11792 0.11337 -0.0515 0.0038 1.0000
16.000 1.2041 0.12403 0.11970 -0.0545 0.0037 1.0000
16.250 1.1956 0.13016 0.12597 -0.0576 0.0037 1.0000
16.500 1.1850 0.13708 0.13308 -0.0613 0.0037 1.0000
16.750 1.1759 0.14384 0.13998 -0.0651 0.0036 1.0000
17.000 1.1665 0.15096 0.14726 -0.0693 0.0036 1.0000
17.250 1.1553 0.15892 0.15538 -0.0741 0.0037 1.0000
17.500 1.1418 0.16817 0.16477 -0.0797 0.0038 1.0000
17.750 1.1301 0.17734 0.17409 -0.0853 0.0039 1.0000
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Polar data table (+)
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