GOE 244 (MVA PR.4) AIRFOIL (goe244-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 244 (MVA PR.4) AIRFOIL (goe244-il) Reynolds number: 100,000 Max Cl/Cd: 47.84 at α=0.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe244-il-100000-n5.txt Download as CSV file: xf-goe244-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 244 (MVA PR.4) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 0.2568 0.11133 0.10574 -0.1288 0.8684 0.0720
-9.750 0.2527 0.11030 0.10474 -0.1294 0.8604 0.0724
-9.500 0.2609 0.10780 0.10226 -0.1301 0.8553 0.0727
-9.250 0.2802 0.10452 0.09896 -0.1303 0.8522 0.0735
-9.000 0.2962 0.10177 0.09620 -0.1314 0.8494 0.0744
-8.750 0.2996 0.10034 0.09481 -0.1304 0.8413 0.0753
-8.500 0.3089 0.09816 0.09263 -0.1310 0.8357 0.0766
-8.250 0.3191 0.09572 0.09016 -0.1327 0.8316 0.0785
-8.000 0.3085 0.09507 0.08955 -0.1329 0.8221 0.0800
-7.750 0.3055 0.09321 0.08770 -0.1345 0.8152 0.0805
-7.500 0.3370 0.08930 0.08375 -0.1343 0.8122 0.0818
-7.250 0.3414 0.08784 0.08232 -0.1326 0.8029 0.0828
-7.000 0.3513 0.08564 0.08010 -0.1328 0.7965 0.0838
-6.750 0.3647 0.08297 0.07738 -0.1343 0.7921 0.0848
-6.250 0.3661 0.07977 0.07422 -0.1324 0.7751 0.0859
-5.750 0.3418 0.07312 0.06754 -0.1327 0.7580 0.0592
-5.250 0.3400 0.06775 0.06221 -0.1335 0.7432 0.0541
-5.000 0.3558 0.06517 0.05960 -0.1353 0.7380 0.0532
-4.750 0.3815 0.06128 0.05563 -0.1408 0.7344 0.0524
-4.500 0.3658 0.06023 0.05468 -0.1377 0.7228 0.0522
-4.250 0.5454 0.03427 0.02706 -0.2095 0.7202 0.0493
-4.000 0.6082 0.03136 0.02365 -0.2185 0.7166 0.0495
-3.750 0.6385 0.03030 0.02239 -0.2204 0.7086 0.0498
-3.500 0.6765 0.02910 0.02097 -0.2230 0.7020 0.0502
-3.250 0.7219 0.02775 0.01938 -0.2265 0.6972 0.0509
-3.000 0.7461 0.02733 0.01887 -0.2264 0.6882 0.0517
-2.750 0.7820 0.02654 0.01789 -0.2279 0.6810 0.0534
-2.500 0.8156 0.02597 0.01726 -0.2290 0.6737 0.0550
-2.250 0.8411 0.02572 0.01699 -0.2287 0.6643 0.0565
-2.000 0.8809 0.02501 0.01614 -0.2306 0.6580 0.0582
-1.750 0.9012 0.02503 0.01614 -0.2294 0.6469 0.0595
-1.500 0.9395 0.02449 0.01552 -0.2312 0.6389 0.0617
-1.250 0.9617 0.02454 0.01553 -0.2304 0.6270 0.0641
-1.000 0.9960 0.02420 0.01505 -0.2316 0.6170 0.0683
-0.750 1.0220 0.02415 0.01493 -0.2315 0.6045 0.0751
-0.500 1.0515 0.02398 0.01467 -0.2321 0.5924 0.0881
-0.250 1.0917 0.02335 0.01435 -0.2352 0.5803 0.1966
0.000 1.1113 0.02363 0.01467 -0.2339 0.5664 0.2604
0.250 1.1327 0.02389 0.01489 -0.2329 0.5532 0.2965
0.500 1.1549 0.02415 0.01506 -0.2318 0.5402 0.3237
0.750 1.1740 0.02454 0.01539 -0.2303 0.5264 0.3452
1.000 1.1933 0.02500 0.01579 -0.2289 0.5132 0.3679
1.250 1.2135 0.02544 0.01614 -0.2276 0.5014 0.3887
1.500 1.2331 0.02594 0.01654 -0.2262 0.4899 0.4052
1.750 1.2538 0.02644 0.01690 -0.2251 0.4801 0.4202
2.000 1.2747 0.02694 0.01726 -0.2241 0.4712 0.4360
2.250 1.2959 0.02743 0.01766 -0.2231 0.4637 0.4497
2.500 1.3165 0.02798 0.01812 -0.2220 0.4564 0.4641
2.750 1.3392 0.02846 0.01844 -0.2213 0.4502 0.4793
3.000 1.3608 0.02899 0.01890 -0.2204 0.4446 0.4929
3.250 1.3812 0.02956 0.01944 -0.2195 0.4389 0.5054
3.500 1.4034 0.03008 0.01985 -0.2187 0.4339 0.5192
3.750 1.4280 0.03052 0.02015 -0.2183 0.4295 0.5331
4.000 1.4474 0.03114 0.02078 -0.2172 0.4249 0.5452
4.250 1.4669 0.03178 0.02140 -0.2162 0.4202 0.5582
4.500 1.4875 0.03237 0.02195 -0.2153 0.4160 0.5704
4.750 1.5110 0.03285 0.02236 -0.2147 0.4124 0.5829
5.000 1.5389 0.03325 0.02260 -0.2148 0.4093 0.5967
5.250 1.5557 0.03399 0.02344 -0.2135 0.4060 0.6084
5.500 1.5742 0.03471 0.02420 -0.2124 0.4027 0.6207
6.000 1.6140 0.03603 0.02556 -0.2107 0.3967 0.6476
6.250 1.6363 0.03660 0.02612 -0.2101 0.3940 0.6624
6.500 1.6614 0.03708 0.02656 -0.2099 0.3917 0.6788
6.750 1.6895 0.03749 0.02691 -0.2102 0.3893 0.6965
7.000 1.7003 0.03853 0.02811 -0.2083 0.3866 0.7113
7.250 1.7126 0.03953 0.02924 -0.2066 0.3837 0.7270
7.750 1.7423 0.04127 0.03122 -0.2040 0.3785 0.7771
8.000 1.7549 0.04189 0.03197 -0.2022 0.3762 1.0000
8.250 1.7756 0.04268 0.03271 -0.2017 0.3737 1.0000
8.500 1.8001 0.04327 0.03319 -0.2016 0.3711 1.0000
8.750 1.8127 0.04443 0.03439 -0.2002 0.3682 1.0000
9.000 1.8093 0.04638 0.03652 -0.1971 0.3650 1.0000
9.250 1.8105 0.04817 0.03842 -0.1947 0.3615 1.0000
9.500 1.8172 0.04962 0.03993 -0.1929 0.3580 1.0000
9.750 1.8306 0.05066 0.04095 -0.1916 0.3548 1.0000
10.000 1.8509 0.05127 0.04151 -0.1910 0.3520 1.0000
10.250 1.8636 0.05245 0.04270 -0.1898 0.3492 1.0000
10.500 1.8461 0.05572 0.04624 -0.1862 0.3460 1.0000
10.750 1.8344 0.05878 0.04948 -0.1834 0.3425 1.0000
11.000 1.8311 0.06123 0.05205 -0.1813 0.3390 1.0000
11.250 1.8397 0.06267 0.05353 -0.1800 0.3357 1.0000
11.500 1.8591 0.06316 0.05397 -0.1793 0.3329 1.0000
11.750 1.8679 0.06467 0.05550 -0.1781 0.3301 1.0000
12.000 1.8169 0.07211 0.06336 -0.1743 0.3259 1.0000
12.250 1.7757 0.07934 0.07088 -0.1719 0.3212 1.0000
12.500 1.7706 0.08265 0.07429 -0.1709 0.3176 1.0000
12.750 1.7916 0.08281 0.07442 -0.1703 0.3151 1.0000
13.000 1.8226 0.08179 0.07333 -0.1699 0.3131 1.0000
13.250 1.6095 0.11448 0.10686 -0.1708 0.2967 1.0000
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Polar data table (+)
Polar graphs
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