GOE 330 (PFALZ 59) AIRFOIL (goe330-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 330 (PFALZ 59) AIRFOIL (goe330-il) Reynolds number: 500,000 Max Cl/Cd: 103.89 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe330-il-500000.txt Download as CSV file: xf-goe330-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 330 (PFALZ 59) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.1378 0.08496 0.08273 -0.0709 0.9737 0.0233
-8.000 -0.1237 0.08124 0.07901 -0.0753 0.9649 0.0246
-7.750 -0.1146 0.07694 0.07468 -0.0846 0.9488 0.0254
-7.500 -0.0995 0.07263 0.07033 -0.0909 0.9381 0.0255
-7.250 -0.0916 0.06781 0.06549 -0.0936 0.9290 0.0258
-7.000 -0.0806 0.06571 0.06337 -0.0925 0.9211 0.0262
-6.750 -0.0664 0.06341 0.06103 -0.0933 0.9133 0.0267
-6.500 -0.0499 0.06064 0.05822 -0.0960 0.9044 0.0274
-6.250 -0.0305 0.05740 0.05490 -0.0998 0.8969 0.0284
-6.000 0.0092 0.05117 0.04846 -0.1125 0.8878 0.0313
-5.750 0.0301 0.04481 0.04190 -0.1178 0.8812 0.0318
-5.500 0.0462 0.04290 0.03998 -0.1177 0.8737 0.0324
-5.250 0.0665 0.04118 0.03818 -0.1183 0.8673 0.0331
-5.000 0.0893 0.03893 0.03585 -0.1197 0.8599 0.0342
-4.750 0.1154 0.03609 0.03283 -0.1217 0.8530 0.0363
-4.500 0.1463 0.03036 0.02658 -0.1249 0.8457 0.0395
-4.250 0.1682 0.02890 0.02508 -0.1250 0.8386 0.0403
-4.000 0.1916 0.02770 0.02382 -0.1252 0.8312 0.0415
-3.750 0.2167 0.02614 0.02209 -0.1253 0.8232 0.0439
-3.500 0.2444 0.02321 0.01862 -0.1254 0.8156 0.0486
-3.250 0.2684 0.02187 0.01724 -0.1254 0.8078 0.0496
-3.000 0.2934 0.02086 0.01615 -0.1253 0.8001 0.0511
-2.750 0.3196 0.01993 0.01505 -0.1250 0.7919 0.0545
-2.500 0.3463 0.01845 0.01318 -0.1245 0.7831 0.0594
-2.250 0.3717 0.01733 0.01198 -0.1244 0.7742 0.0608
-2.000 0.3994 0.01419 0.00828 -0.1231 0.7644 0.0450
-1.750 0.4259 0.01235 0.00608 -0.1224 0.7547 0.0416
-1.500 0.4525 0.01173 0.00533 -0.1220 0.7438 0.0420
-1.250 0.4789 0.01115 0.00465 -0.1215 0.7308 0.0424
-1.000 0.5051 0.01062 0.00402 -0.1210 0.7167 0.0425
-0.750 0.5311 0.01026 0.00357 -0.1205 0.7017 0.0432
-0.500 0.5569 0.01000 0.00322 -0.1200 0.6867 0.0440
-0.250 0.5828 0.00981 0.00295 -0.1195 0.6725 0.0451
0.000 0.6085 0.00969 0.00273 -0.1189 0.6581 0.0462
0.250 0.6343 0.00965 0.00260 -0.1184 0.6440 0.0475
0.500 0.6599 0.00954 0.00245 -0.1180 0.6303 0.0512
0.750 0.6860 0.00956 0.00241 -0.1175 0.6173 0.0553
1.000 0.7119 0.00956 0.00238 -0.1171 0.6044 0.0636
1.250 0.7376 0.00954 0.00232 -0.1167 0.5905 0.0867
1.500 0.7632 0.00953 0.00233 -0.1162 0.5745 0.1114
1.750 0.7814 0.00828 0.00258 -0.1150 0.5577 0.7253
2.000 0.8260 0.00801 0.00266 -0.1184 0.5335 1.0000
2.250 0.8493 0.00822 0.00273 -0.1175 0.5087 1.0000
2.500 0.8717 0.00849 0.00282 -0.1165 0.4839 1.0000
2.750 0.8948 0.00876 0.00295 -0.1156 0.4644 1.0000
3.000 0.9182 0.00903 0.00309 -0.1147 0.4502 1.0000
3.250 0.9417 0.00929 0.00325 -0.1140 0.4385 1.0000
3.500 0.9660 0.00952 0.00342 -0.1133 0.4284 1.0000
3.750 0.9903 0.00975 0.00359 -0.1127 0.4203 1.0000
4.000 1.0147 0.00997 0.00376 -0.1121 0.4125 1.0000
4.250 1.0392 0.01020 0.00394 -0.1116 0.4058 1.0000
4.500 1.0640 0.01040 0.00413 -0.1111 0.3991 1.0000
4.750 1.0877 0.01067 0.00434 -0.1104 0.3927 1.0000
5.000 1.1131 0.01082 0.00452 -0.1100 0.3867 1.0000
5.250 1.1374 0.01105 0.00473 -0.1095 0.3809 1.0000
5.500 1.1616 0.01128 0.00495 -0.1089 0.3756 1.0000
5.750 1.1864 0.01145 0.00514 -0.1084 0.3691 1.0000
6.000 1.2095 0.01172 0.00537 -0.1077 0.3613 1.0000
6.250 1.2341 0.01188 0.00557 -0.1072 0.3530 1.0000
6.500 1.2572 0.01213 0.00580 -0.1065 0.3446 1.0000
6.750 1.2809 0.01233 0.00601 -0.1059 0.3358 1.0000
7.000 1.3041 0.01256 0.00626 -0.1052 0.3268 1.0000
7.250 1.3260 0.01285 0.00652 -0.1044 0.3149 1.0000
7.500 1.3476 0.01315 0.00679 -0.1034 0.3008 1.0000
7.750 1.3687 0.01348 0.00709 -0.1024 0.2831 1.0000
8.000 1.3867 0.01399 0.00748 -0.1010 0.2578 1.0000
8.250 1.3991 0.01476 0.00803 -0.0986 0.2170 1.0000
8.500 1.4047 0.01596 0.00891 -0.0952 0.1741 1.0000
8.750 1.4103 0.01719 0.00989 -0.0919 0.1346 1.0000
9.000 1.3922 0.01998 0.01202 -0.0855 0.0365 1.0000
9.250 1.4003 0.02113 0.01317 -0.0828 0.0264 1.0000
9.500 1.4122 0.02204 0.01417 -0.0808 0.0239 1.0000
9.750 1.4212 0.02317 0.01538 -0.0785 0.0219 1.0000
10.000 1.4304 0.02432 0.01663 -0.0764 0.0208 1.0000
10.250 1.4407 0.02541 0.01780 -0.0745 0.0198 1.0000
10.500 1.4493 0.02665 0.01913 -0.0726 0.0188 1.0000
10.750 1.4557 0.02811 0.02067 -0.0706 0.0180 1.0000
11.000 1.4585 0.02991 0.02256 -0.0685 0.0173 1.0000
11.250 1.4559 0.03223 0.02501 -0.0661 0.0168 1.0000
11.500 1.4501 0.03495 0.02785 -0.0638 0.0164 1.0000
11.750 1.4543 0.03688 0.02989 -0.0624 0.0161 1.0000
12.000 1.4555 0.03915 0.03226 -0.0610 0.0158 1.0000
12.250 1.4550 0.04168 0.03490 -0.0597 0.0155 1.0000
12.500 1.4537 0.04442 0.03774 -0.0586 0.0151 1.0000
12.750 1.4515 0.04736 0.04079 -0.0578 0.0148 1.0000
13.000 1.4494 0.05043 0.04396 -0.0572 0.0144 1.0000
13.250 1.4466 0.05369 0.04732 -0.0567 0.0141 1.0000
13.500 1.4430 0.05714 0.05086 -0.0565 0.0138 1.0000
13.750 1.4380 0.06083 0.05463 -0.0563 0.0135 1.0000
14.000 1.4317 0.06472 0.05860 -0.0562 0.0133 1.0000
14.250 1.4244 0.06873 0.06269 -0.0561 0.0131 1.0000
14.500 1.4167 0.07266 0.06668 -0.0558 0.0129 1.0000
14.750 1.4105 0.07588 0.06993 -0.0544 0.0126 1.0000
15.000 1.4117 0.07904 0.07319 -0.0546 0.0125 1.0000
15.250 1.4126 0.08213 0.07638 -0.0547 0.0123 1.0000
15.500 1.4138 0.08516 0.07952 -0.0547 0.0122 1.0000
15.750 1.4153 0.08809 0.08254 -0.0547 0.0120 1.0000
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Polar data table (+)
Polar graphs
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