GOE 411 AIRFOIL (goe411-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 411 AIRFOIL (goe411-il) Reynolds number: 100,000 Max Cl/Cd: 34.1 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe411-il-100000-n5.txt Download as CSV file: xf-goe411-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 411 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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.6708 0.08631 0.08068 -0.0482 1.0000 0.0163
-12.250 -0.6878 0.08080 0.07506 -0.0506 1.0000 0.0162
-12.000 -0.7052 0.07584 0.06997 -0.0524 1.0000 0.0160
-11.750 -0.7217 0.07155 0.06555 -0.0534 1.0000 0.0160
-11.500 -0.7383 0.06752 0.06136 -0.0535 1.0000 0.0158
-11.250 -0.7544 0.06404 0.05772 -0.0527 1.0000 0.0158
-11.000 -0.7701 0.06098 0.05447 -0.0510 1.0000 0.0157
-10.750 -0.7837 0.05826 0.05158 -0.0485 1.0000 0.0156
-10.500 -0.7971 0.05580 0.04894 -0.0453 1.0000 0.0156
-10.250 -0.8103 0.05344 0.04637 -0.0412 1.0000 0.0155
-10.000 -0.8220 0.05141 0.04415 -0.0366 1.0000 0.0155
-9.750 -0.8299 0.04945 0.04199 -0.0322 1.0000 0.0155
-9.500 -0.8335 0.04718 0.03948 -0.0283 1.0000 0.0154
-9.250 -0.8340 0.04508 0.03713 -0.0246 1.0000 0.0154
-9.000 -0.8311 0.04299 0.03478 -0.0211 1.0000 0.0154
-8.750 -0.8261 0.04125 0.03279 -0.0178 1.0000 0.0156
-8.500 -0.8216 0.04011 0.03137 -0.0141 1.0000 0.0162
-8.250 -0.8145 0.03851 0.02953 -0.0109 1.0000 0.0167
-8.000 -0.7931 0.03517 0.02604 -0.0103 1.0000 0.0174
-7.750 -0.7733 0.03304 0.02374 -0.0091 1.0000 0.0178
-7.500 -0.7562 0.03130 0.02196 -0.0074 1.0000 0.0181
-7.250 -0.7438 0.02988 0.02050 -0.0049 1.0000 0.0185
-7.000 -0.7359 0.02858 0.01918 -0.0016 1.0000 0.0189
-6.750 -0.7300 0.02747 0.01802 0.0021 1.0000 0.0194
-6.500 -0.7251 0.02645 0.01691 0.0059 1.0000 0.0202
-6.250 -0.7193 0.02551 0.01588 0.0096 1.0000 0.0217
-6.000 -0.7117 0.02469 0.01493 0.0131 1.0000 0.0229
-5.750 -0.7031 0.02387 0.01395 0.0165 1.0000 0.0242
-5.500 -0.6926 0.02315 0.01305 0.0195 1.0000 0.0251
-5.250 -0.6805 0.02252 0.01224 0.0223 1.0000 0.0260
-5.000 -0.6688 0.02180 0.01136 0.0252 1.0000 0.0282
-4.750 -0.6565 0.02111 0.01051 0.0279 1.0000 0.0322
-4.500 -0.6348 0.02029 0.00970 0.0287 0.9972 0.0434
-4.250 -0.6152 0.01833 0.00889 0.0287 0.9908 0.2319
-4.000 -0.5907 0.01729 0.00860 0.0285 0.9844 0.3629
-3.750 -0.5627 0.01680 0.00850 0.0280 0.9780 0.4580
-3.500 -0.5371 0.01646 0.00842 0.0283 0.9703 0.5335
-3.250 -0.5077 0.01624 0.00826 0.0279 0.9632 0.5759
-3.000 -0.4713 0.01609 0.00805 0.0260 0.9577 0.5969
-2.750 -0.4396 0.01592 0.00784 0.0251 0.9500 0.6177
-2.500 -0.4057 0.01575 0.00767 0.0238 0.9429 0.6400
-2.250 -0.3686 0.01562 0.00755 0.0219 0.9367 0.6645
-2.000 -0.3359 0.01550 0.00751 0.0211 0.9285 0.6947
-1.750 -0.2946 0.01543 0.00752 0.0187 0.9233 0.7312
-1.500 -0.2613 0.01541 0.00755 0.0179 0.9142 0.7633
-1.250 -0.2151 0.01538 0.00752 0.0144 0.9094 0.7875
-1.000 -0.1797 0.01537 0.00751 0.0131 0.8994 0.8081
-0.750 -0.1334 0.01536 0.00748 0.0095 0.8931 0.8249
-0.500 -0.0900 0.01539 0.00751 0.0065 0.8839 0.8399
-0.250 -0.0467 0.01540 0.00752 0.0036 0.8742 0.8534
0.000 0.0001 0.01538 0.00749 0.0000 0.8651 0.8651
0.250 0.0466 0.01540 0.00752 -0.0036 0.8535 0.8741
0.500 0.0900 0.01539 0.00751 -0.0065 0.8399 0.8839
0.750 0.1333 0.01536 0.00748 -0.0095 0.8249 0.8931
1.000 0.1797 0.01536 0.00750 -0.0130 0.8080 0.8995
1.250 0.2152 0.01538 0.00752 -0.0144 0.7876 0.9094
1.500 0.2613 0.01540 0.00755 -0.0179 0.7637 0.9141
1.750 0.2946 0.01543 0.00752 -0.0187 0.7315 0.9233
2.000 0.3359 0.01550 0.00749 -0.0211 0.6944 0.9285
2.250 0.3686 0.01561 0.00755 -0.0219 0.6644 0.9367
2.500 0.4057 0.01575 0.00767 -0.0238 0.6397 0.9430
2.750 0.4395 0.01591 0.00784 -0.0251 0.6178 0.9500
3.000 0.4712 0.01608 0.00805 -0.0260 0.5969 0.9577
3.250 0.5077 0.01623 0.00826 -0.0279 0.5758 0.9632
3.500 0.5367 0.01646 0.00842 -0.0282 0.5312 0.9704
3.750 0.5629 0.01679 0.00850 -0.0280 0.4597 0.9780
4.000 0.5903 0.01731 0.00859 -0.0284 0.3583 0.9846
4.250 0.6150 0.01834 0.00889 -0.0287 0.2301 0.9909
4.500 0.6346 0.02033 0.00972 -0.0287 0.0425 0.9973
4.750 0.6567 0.02107 0.01046 -0.0279 0.0329 1.0000
5.000 0.6686 0.02180 0.01136 -0.0252 0.0282 1.0000
5.250 0.6803 0.02253 0.01226 -0.0223 0.0259 1.0000
5.500 0.6924 0.02316 0.01306 -0.0195 0.0251 1.0000
5.750 0.7028 0.02389 0.01397 -0.0164 0.0240 1.0000
6.000 0.7116 0.02468 0.01491 -0.0131 0.0227 1.0000
6.250 0.7191 0.02551 0.01588 -0.0096 0.0213 1.0000
6.500 0.7250 0.02644 0.01690 -0.0059 0.0200 1.0000
6.750 0.7305 0.02742 0.01797 -0.0022 0.0195 1.0000
7.000 0.7358 0.02857 0.01917 0.0016 0.0189 1.0000
7.250 0.7440 0.02979 0.02042 0.0048 0.0186 1.0000
7.500 0.7561 0.03125 0.02191 0.0074 0.0182 1.0000
7.750 0.7729 0.03296 0.02366 0.0092 0.0178 1.0000
8.000 0.7925 0.03502 0.02588 0.0104 0.0175 1.0000
8.250 0.8129 0.03794 0.02895 0.0113 0.0169 1.0000
8.500 0.8223 0.04021 0.03147 0.0140 0.0162 1.0000
8.750 0.8268 0.04134 0.03287 0.0177 0.0157 1.0000
9.000 0.8318 0.04301 0.03479 0.0210 0.0155 1.0000
9.250 0.8341 0.04504 0.03708 0.0246 0.0154 1.0000
9.500 0.8334 0.04718 0.03948 0.0283 0.0154 1.0000
9.750 0.8302 0.04940 0.04194 0.0322 0.0155 1.0000
10.000 0.8224 0.05140 0.04413 0.0366 0.0155 1.0000
10.250 0.8100 0.05350 0.04644 0.0412 0.0155 1.0000
10.500 0.7973 0.05573 0.04886 0.0452 0.0155 1.0000
10.750 0.7844 0.05820 0.05151 0.0485 0.0156 1.0000
11.000 0.7696 0.06107 0.05457 0.0510 0.0157 1.0000
11.250 0.7549 0.06408 0.05775 0.0526 0.0158 1.0000
11.500 0.7388 0.06752 0.06137 0.0534 0.0158 1.0000
11.750 0.7217 0.07158 0.06558 0.0533 0.0159 1.0000
12.000 0.7067 0.07574 0.06986 0.0523 0.0161 1.0000
12.250 0.6883 0.08094 0.07519 0.0505 0.0162 1.0000
13.500 0.6217 0.10940 0.10417 0.0344 0.0171 1.0000
13.750 0.6049 0.11831 0.11314 0.0288 0.0174 1.0000
14.000 0.5833 0.13203 0.12687 0.0215 0.0190 1.0000
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