GOE 300 (FRIEDRICHSHAFEN G20) AIRFOIL (goe300-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 300 (FRIEDRICHSHAFEN G20) AIRFOIL (goe300-il) Reynolds number: 200,000 Max Cl/Cd: 81.17 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe300-il-200000-n5.txt Download as CSV file: xf-goe300-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 300 (FRIEDRICHSHAFEN G20) 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 -0.1332 0.08199 0.07860 -0.0599 0.9238 0.0205
-7.250 -0.1201 0.07880 0.07538 -0.0626 0.9125 0.0203
-7.000 -0.1068 0.07423 0.07077 -0.0685 0.8991 0.0207
-6.750 -0.0921 0.07330 0.06984 -0.0674 0.8880 0.0219
-6.500 -0.0760 0.07030 0.06680 -0.0705 0.8761 0.0225
-6.250 -0.0584 0.06654 0.06297 -0.0747 0.8644 0.0223
-6.000 -0.0387 0.06263 0.05899 -0.0792 0.8520 0.0222
-5.750 -0.0167 0.05883 0.05511 -0.0836 0.8404 0.0224
-5.500 0.0073 0.05524 0.05141 -0.0877 0.8294 0.0232
-5.250 0.0360 0.05043 0.04642 -0.0937 0.8180 0.0247
-5.000 0.0682 0.04396 0.03969 -0.1005 0.8067 0.0256
-4.750 0.0924 0.04259 0.03824 -0.1015 0.7948 0.0265
-4.500 0.1180 0.04106 0.03657 -0.1027 0.7822 0.0283
-4.250 0.1506 0.03645 0.03165 -0.1066 0.7698 0.0306
-4.000 0.1807 0.03313 0.02804 -0.1089 0.7572 0.0330
-3.750 0.2066 0.03227 0.02705 -0.1092 0.7435 0.0350
-3.500 0.2414 0.02672 0.02089 -0.1121 0.7320 0.0405
-3.250 0.2665 0.02674 0.02081 -0.1118 0.7182 0.0420
-3.000 0.2935 0.02579 0.01966 -0.1120 0.7047 0.0447
-2.750 0.3251 0.02213 0.01540 -0.1130 0.6933 0.0509
-2.500 0.3507 0.02224 0.01545 -0.1127 0.6799 0.0527
-2.250 0.3778 0.02150 0.01448 -0.1126 0.6680 0.0557
-2.000 0.4080 0.01914 0.01150 -0.1128 0.6575 0.0611
-1.750 0.4347 0.01850 0.01073 -0.1128 0.6477 0.0626
-1.500 0.4615 0.01833 0.01047 -0.1127 0.6378 0.0645
-1.250 0.4888 0.01786 0.00984 -0.1125 0.6283 0.0669
-0.750 0.5443 0.01640 0.00790 -0.1122 0.6111 0.0703
-0.250 0.5993 0.01547 0.00659 -0.1119 0.5952 0.0740
0.000 0.6263 0.01516 0.00618 -0.1117 0.5876 0.0751
0.250 0.6535 0.01492 0.00589 -0.1115 0.5795 0.0764
0.500 0.6804 0.01474 0.00562 -0.1112 0.5717 0.0779
0.750 0.7075 0.01455 0.00539 -0.1110 0.5635 0.0794
1.000 0.7343 0.01441 0.00517 -0.1107 0.5555 0.0811
1.250 0.7611 0.01432 0.00504 -0.1104 0.5472 0.0837
1.500 0.7877 0.01430 0.00493 -0.1101 0.5384 0.0860
1.750 0.8142 0.01413 0.00479 -0.1099 0.5290 0.0881
2.000 0.8404 0.01409 0.00473 -0.1095 0.5201 0.0904
2.250 0.8669 0.01406 0.00472 -0.1093 0.5107 0.0933
2.500 0.8931 0.01408 0.00472 -0.1089 0.5021 0.0969
2.750 0.9194 0.01411 0.00473 -0.1086 0.4920 0.1006
3.000 0.9454 0.01412 0.00477 -0.1083 0.4813 0.1057
3.250 0.9710 0.01421 0.00484 -0.1079 0.4698 0.1123
3.500 0.9968 0.01430 0.00493 -0.1076 0.4581 0.1218
3.750 1.0226 0.01441 0.00505 -0.1073 0.4475 0.1338
4.000 1.0480 0.01454 0.00518 -0.1069 0.4373 0.1487
4.250 1.0734 0.01464 0.00535 -0.1065 0.4269 0.1813
4.750 1.1222 0.01386 0.00577 -0.1054 0.4072 1.0000
5.000 1.1470 0.01413 0.00599 -0.1049 0.3966 1.0000
5.250 1.1712 0.01443 0.00623 -0.1043 0.3863 1.0000
5.500 1.1951 0.01475 0.00650 -0.1037 0.3772 1.0000
5.750 1.2195 0.01505 0.00678 -0.1032 0.3693 1.0000
6.000 1.2432 0.01539 0.00710 -0.1026 0.3617 1.0000
6.250 1.2672 0.01572 0.00743 -0.1021 0.3553 1.0000
6.500 1.2906 0.01607 0.00778 -0.1015 0.3478 1.0000
6.750 1.3135 0.01644 0.00816 -0.1008 0.3403 1.0000
7.000 1.3365 0.01681 0.00854 -0.1001 0.3322 1.0000
7.250 1.3586 0.01722 0.00895 -0.0994 0.3253 1.0000
7.500 1.3815 0.01757 0.00938 -0.0987 0.3180 1.0000
7.750 1.4024 0.01804 0.00984 -0.0978 0.3104 1.0000
8.000 1.4246 0.01839 0.01028 -0.0970 0.3016 1.0000
8.250 1.4445 0.01887 0.01079 -0.0960 0.2927 1.0000
8.500 1.4651 0.01929 0.01129 -0.0950 0.2820 1.0000
8.750 1.4844 0.01976 0.01182 -0.0938 0.2701 1.0000
9.000 1.5023 0.02029 0.01238 -0.0925 0.2562 1.0000
9.250 1.5182 0.02089 0.01301 -0.0909 0.2391 1.0000
9.500 1.5298 0.02163 0.01371 -0.0887 0.2206 1.0000
9.750 1.5390 0.02253 0.01455 -0.0862 0.2046 1.0000
10.000 1.5467 0.02358 0.01556 -0.0837 0.1920 1.0000
10.250 1.5536 0.02474 0.01670 -0.0813 0.1817 1.0000
10.500 1.5591 0.02605 0.01801 -0.0790 0.1729 1.0000
10.750 1.5652 0.02740 0.01938 -0.0768 0.1647 1.0000
11.000 1.5710 0.02882 0.02083 -0.0748 0.1581 1.0000
11.250 1.5793 0.03012 0.02222 -0.0732 0.1511 1.0000
11.500 1.5828 0.03184 0.02397 -0.0714 0.1454 1.0000
11.750 1.5933 0.03307 0.02534 -0.0702 0.1398 1.0000
12.000 1.6007 0.03460 0.02698 -0.0689 0.1335 1.0000
12.250 1.6049 0.03645 0.02890 -0.0676 0.1276 1.0000
12.500 1.6127 0.03807 0.03063 -0.0667 0.1187 1.0000
12.750 1.6155 0.04020 0.03280 -0.0657 0.1076 1.0000
13.000 1.6150 0.04274 0.03535 -0.0647 0.0947 1.0000
13.250 1.6090 0.04597 0.03853 -0.0638 0.0793 1.0000
13.500 1.5977 0.04987 0.04236 -0.0630 0.0610 1.0000
13.750 1.5781 0.05489 0.04725 -0.0625 0.0391 1.0000
14.000 1.5632 0.05958 0.05192 -0.0622 0.0312 1.0000
14.250 1.5533 0.06385 0.05628 -0.0621 0.0273 1.0000
14.500 1.5431 0.06832 0.06086 -0.0623 0.0247 1.0000
14.750 1.5336 0.07279 0.06546 -0.0627 0.0229 1.0000
15.000 1.5260 0.07713 0.06996 -0.0632 0.0215 1.0000
15.250 1.5167 0.08181 0.07478 -0.0639 0.0204 1.0000
15.500 1.5058 0.08682 0.07993 -0.0648 0.0195 1.0000
15.750 1.4934 0.09219 0.08544 -0.0660 0.0189 1.0000
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Polar data table (+)
Polar graphs
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