GOE 414 AIRFOIL (goe414-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 414 AIRFOIL (goe414-il) Reynolds number: 500,000 Max Cl/Cd: 100.03 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe414-il-500000.txt Download as CSV file: xf-goe414-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 414 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2197 0.10413 0.10189 -0.0700 0.9877 0.0283
-10.500 -0.4440 0.03657 0.03369 -0.1270 0.9634 0.0184
-10.250 -0.4419 0.03180 0.02842 -0.1298 0.9561 0.0188
-10.000 -0.4352 0.02939 0.02564 -0.1290 0.9469 0.0191
-9.750 -0.4275 0.02604 0.02185 -0.1285 0.9407 0.0196
-9.500 -0.4135 0.02432 0.02001 -0.1273 0.9329 0.0202
-9.250 -0.3926 0.02333 0.01891 -0.1268 0.9278 0.0208
-9.000 -0.3720 0.02245 0.01792 -0.1262 0.9218 0.0216
-8.750 -0.3503 0.02157 0.01687 -0.1256 0.9160 0.0226
-8.500 -0.3270 0.02075 0.01582 -0.1250 0.9115 0.0236
-8.250 -0.3063 0.01960 0.01441 -0.1242 0.9045 0.0244
-8.000 -0.2864 0.01787 0.01255 -0.1234 0.8987 0.0256
-7.750 -0.2626 0.01714 0.01174 -0.1229 0.8928 0.0267
-7.500 -0.2382 0.01647 0.01096 -0.1225 0.8864 0.0279
-7.250 -0.2122 0.01593 0.01028 -0.1222 0.8815 0.0294
-7.000 -0.1872 0.01539 0.00959 -0.1217 0.8745 0.0304
-6.750 -0.1645 0.01408 0.00816 -0.1210 0.8684 0.0323
-6.500 -0.1392 0.01351 0.00754 -0.1207 0.8618 0.0338
-6.250 -0.1133 0.01305 0.00699 -0.1203 0.8549 0.0356
-6.000 -0.0869 0.01267 0.00649 -0.1200 0.8475 0.0371
-5.750 -0.0618 0.01201 0.00573 -0.1195 0.8396 0.0390
-5.500 -0.0360 0.01154 0.00522 -0.1192 0.8320 0.0414
-5.250 -0.0093 0.01122 0.00481 -0.1189 0.8239 0.0440
-5.000 0.0173 0.01093 0.00444 -0.1186 0.8150 0.0462
-4.750 0.0441 0.01059 0.00406 -0.1183 0.8070 0.0515
-4.500 0.0708 0.01033 0.00383 -0.1181 0.7977 0.0608
-4.250 0.0983 0.01019 0.00368 -0.1180 0.7893 0.0785
-4.000 0.1257 0.01008 0.00356 -0.1179 0.7797 0.0915
-3.750 0.1529 0.00996 0.00342 -0.1178 0.7700 0.1005
-3.500 0.1805 0.00995 0.00330 -0.1177 0.7601 0.1065
-3.250 0.2072 0.00979 0.00313 -0.1175 0.7491 0.1130
-3.000 0.2343 0.00972 0.00300 -0.1173 0.7379 0.1184
-2.750 0.2614 0.00964 0.00285 -0.1171 0.7271 0.1242
-2.500 0.2881 0.00955 0.00273 -0.1169 0.7164 0.1325
-2.250 0.3150 0.00946 0.00262 -0.1168 0.7053 0.1419
-2.000 0.3417 0.00936 0.00251 -0.1166 0.6949 0.1554
-1.750 0.3680 0.00924 0.00242 -0.1164 0.6850 0.1812
-1.500 0.3940 0.00905 0.00239 -0.1161 0.6750 0.2389
-1.250 0.4204 0.00896 0.00240 -0.1160 0.6656 0.2916
-1.000 0.4467 0.00893 0.00239 -0.1157 0.6565 0.3276
-0.750 0.4734 0.00889 0.00240 -0.1156 0.6471 0.3577
-0.500 0.4998 0.00887 0.00240 -0.1154 0.6383 0.3893
-0.250 0.5259 0.00881 0.00242 -0.1151 0.6289 0.4291
0.000 0.5510 0.00863 0.00245 -0.1148 0.6196 0.5034
0.250 0.5698 0.00805 0.00254 -0.1130 0.6104 0.7404
0.500 0.6233 0.00778 0.00272 -0.1181 0.5986 0.9800
0.750 0.6718 0.00792 0.00276 -0.1228 0.5859 1.0000
1.000 0.6953 0.00804 0.00279 -0.1220 0.5738 1.0000
1.250 0.7184 0.00817 0.00283 -0.1211 0.5607 1.0000
1.500 0.7413 0.00831 0.00288 -0.1202 0.5468 1.0000
1.750 0.7640 0.00846 0.00294 -0.1192 0.5321 1.0000
2.000 0.7865 0.00863 0.00301 -0.1182 0.5176 1.0000
2.500 0.8323 0.00899 0.00320 -0.1164 0.4939 1.0000
2.750 0.8556 0.00918 0.00332 -0.1156 0.4853 1.0000
3.000 0.8791 0.00937 0.00344 -0.1148 0.4777 1.0000
3.250 0.9031 0.00956 0.00359 -0.1142 0.4715 1.0000
3.500 0.9273 0.00973 0.00373 -0.1136 0.4656 1.0000
3.750 0.9511 0.00996 0.00389 -0.1129 0.4607 1.0000
4.000 0.9761 0.01012 0.00406 -0.1125 0.4567 1.0000
4.250 1.0010 0.01029 0.00422 -0.1121 0.4522 1.0000
4.500 1.0252 0.01051 0.00440 -0.1115 0.4477 1.0000
4.750 1.0496 0.01075 0.00461 -0.1111 0.4439 1.0000
5.000 1.0748 0.01089 0.00480 -0.1107 0.4401 1.0000
5.250 1.0987 0.01109 0.00499 -0.1101 0.4344 1.0000
5.500 1.1217 0.01134 0.00520 -0.1094 0.4274 1.0000
5.750 1.1454 0.01150 0.00540 -0.1088 0.4210 1.0000
6.000 1.1681 0.01178 0.00563 -0.1080 0.4151 1.0000
6.250 1.1914 0.01192 0.00583 -0.1073 0.4082 1.0000
6.500 1.2139 0.01214 0.00606 -0.1066 0.4022 1.0000
6.750 1.2361 0.01236 0.00630 -0.1057 0.3955 1.0000
7.000 1.2571 0.01257 0.00651 -0.1046 0.3863 1.0000
7.250 1.2764 0.01276 0.00673 -0.1032 0.3745 1.0000
7.500 1.2953 0.01300 0.00698 -0.1017 0.3626 1.0000
7.750 1.3126 0.01331 0.00726 -0.1000 0.3432 1.0000
8.000 1.3186 0.01416 0.00780 -0.0965 0.2859 1.0000
8.250 1.3104 0.01596 0.00912 -0.0912 0.2168 1.0000
8.500 1.2993 0.01810 0.01076 -0.0858 0.1339 1.0000
8.750 1.2811 0.02080 0.01300 -0.0799 0.0571 1.0000
9.000 1.2779 0.02272 0.01476 -0.0762 0.0250 1.0000
9.250 1.2891 0.02375 0.01587 -0.0744 0.0226 1.0000
9.500 1.2982 0.02496 0.01714 -0.0725 0.0208 1.0000
9.750 1.3056 0.02634 0.01861 -0.0706 0.0195 1.0000
10.000 1.3150 0.02760 0.01996 -0.0689 0.0188 1.0000
10.250 1.3226 0.02904 0.02148 -0.0673 0.0180 1.0000
10.500 1.3284 0.03068 0.02319 -0.0656 0.0172 1.0000
10.750 1.3318 0.03257 0.02517 -0.0638 0.0165 1.0000
11.000 1.3321 0.03481 0.02750 -0.0621 0.0160 1.0000
11.250 1.3279 0.03756 0.03036 -0.0602 0.0156 1.0000
11.500 1.3197 0.04085 0.03377 -0.0585 0.0153 1.0000
11.750 1.3202 0.04344 0.03646 -0.0574 0.0151 1.0000
12.000 1.3212 0.04606 0.03917 -0.0565 0.0148 1.0000
12.250 1.3209 0.04889 0.04210 -0.0557 0.0146 1.0000
12.500 1.3194 0.05193 0.04523 -0.0550 0.0144 1.0000
12.750 1.3176 0.05506 0.04846 -0.0544 0.0141 1.0000
13.000 1.3156 0.05823 0.05171 -0.0539 0.0139 1.0000
13.250 1.3138 0.06142 0.05499 -0.0534 0.0136 1.0000
13.500 1.3123 0.06462 0.05826 -0.0531 0.0133 1.0000
13.750 1.3113 0.06779 0.06150 -0.0528 0.0130 1.0000
14.000 1.3100 0.07096 0.06472 -0.0525 0.0127 1.0000
14.250 1.3085 0.07412 0.06793 -0.0521 0.0124 1.0000
14.500 1.3076 0.07711 0.07095 -0.0516 0.0122 1.0000
14.750 1.3087 0.07951 0.07336 -0.0505 0.0119 1.0000
15.000 1.3179 0.08006 0.07387 -0.0478 0.0117 1.0000
15.250 1.3227 0.08257 0.07648 -0.0477 0.0116 1.0000
15.500 1.3283 0.08488 0.07889 -0.0474 0.0114 1.0000
15.750 1.3347 0.08702 0.08111 -0.0470 0.0113 1.0000
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