E221 (9.39%) (e221-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: E221 (9.39%) (e221-il) Reynolds number: 200,000 Max Cl/Cd: 62.19 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e221-il-200000-n5.txt Download as CSV file: xf-e221-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E221 (9.39%)
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5460 0.08431 0.08096 -0.0069 1.0000 0.0139
-8.750 -0.5508 0.07901 0.07571 -0.0104 1.0000 0.0139
-8.500 -0.5545 0.07461 0.07136 -0.0137 1.0000 0.0135
-8.250 -0.5666 0.06830 0.06506 -0.0189 1.0000 0.0134
-8.000 -0.5726 0.06237 0.05907 -0.0223 1.0000 0.0132
-7.750 -0.5770 0.05613 0.05270 -0.0246 1.0000 0.0130
-7.500 -0.5799 0.04981 0.04615 -0.0256 1.0000 0.0127
-7.250 -0.5795 0.04389 0.03990 -0.0255 1.0000 0.0123
-7.000 -0.5759 0.03843 0.03402 -0.0244 1.0000 0.0120
-6.750 -0.5691 0.03341 0.02845 -0.0227 1.0000 0.0117
-6.500 -0.5578 0.02941 0.02391 -0.0208 1.0000 0.0116
-6.250 -0.5427 0.02638 0.02040 -0.0190 1.0000 0.0116
-6.000 -0.5252 0.02401 0.01762 -0.0173 1.0000 0.0116
-5.750 -0.5041 0.02206 0.01534 -0.0162 0.9967 0.0118
-5.500 -0.4711 0.02015 0.01310 -0.0174 0.9763 0.0121
-5.250 -0.4380 0.01861 0.01131 -0.0185 0.9549 0.0126
-5.000 -0.4058 0.01733 0.00980 -0.0194 0.9324 0.0133
-4.750 -0.3753 0.01649 0.00879 -0.0197 0.9099 0.0144
-4.500 -0.3494 0.01559 0.00781 -0.0194 0.8878 0.0160
-4.250 -0.3244 0.01493 0.00703 -0.0186 0.8676 0.0173
-4.000 -0.3001 0.01435 0.00627 -0.0176 0.8488 0.0187
-3.750 -0.2761 0.01378 0.00555 -0.0165 0.8317 0.0207
-3.500 -0.2516 0.01332 0.00496 -0.0156 0.8159 0.0255
-3.250 -0.2276 0.01277 0.00445 -0.0147 0.8011 0.0447
-3.000 -0.2034 0.01229 0.00406 -0.0139 0.7870 0.0826
-2.750 -0.1801 0.01168 0.00376 -0.0132 0.7736 0.1590
-2.500 -0.1568 0.01113 0.00352 -0.0125 0.7608 0.2479
-2.250 -0.1330 0.01071 0.00331 -0.0117 0.7485 0.3265
-2.000 -0.1102 0.01024 0.00313 -0.0107 0.7367 0.4234
-1.750 -0.0890 0.00972 0.00297 -0.0093 0.7252 0.5396
-1.250 -0.0382 0.00876 0.00288 -0.0071 0.7024 0.8099
-1.000 0.0290 0.00882 0.00295 -0.0145 0.6902 0.9102
-0.750 0.0690 0.00896 0.00294 -0.0166 0.6786 0.9436
-0.500 0.1060 0.00908 0.00292 -0.0183 0.6669 0.9641
-0.250 0.1456 0.00917 0.00287 -0.0206 0.6546 0.9789
0.000 0.1884 0.00920 0.00278 -0.0238 0.6421 0.9901
0.250 0.2319 0.00921 0.00266 -0.0271 0.6293 0.9993
0.500 0.2584 0.00924 0.00259 -0.0269 0.6176 1.0000
0.750 0.2832 0.00928 0.00254 -0.0263 0.6060 1.0000
1.000 0.3080 0.00934 0.00251 -0.0257 0.5942 1.0000
1.250 0.3330 0.00939 0.00250 -0.0251 0.5817 1.0000
1.500 0.3580 0.00946 0.00251 -0.0245 0.5694 1.0000
1.750 0.3830 0.00954 0.00253 -0.0239 0.5571 1.0000
2.000 0.4080 0.00963 0.00257 -0.0234 0.5446 1.0000
2.250 0.4330 0.00973 0.00262 -0.0228 0.5319 1.0000
2.500 0.4580 0.00984 0.00268 -0.0222 0.5189 1.0000
2.750 0.4829 0.00996 0.00275 -0.0216 0.5055 1.0000
3.000 0.5079 0.01009 0.00286 -0.0210 0.4918 1.0000
3.250 0.5328 0.01023 0.00296 -0.0204 0.4774 1.0000
3.500 0.5576 0.01038 0.00309 -0.0199 0.4629 1.0000
3.750 0.5824 0.01054 0.00323 -0.0193 0.4481 1.0000
4.000 0.6072 0.01072 0.00340 -0.0187 0.4330 1.0000
4.250 0.6318 0.01090 0.00358 -0.0181 0.4169 1.0000
4.500 0.6563 0.01110 0.00377 -0.0174 0.4003 1.0000
4.750 0.6806 0.01133 0.00399 -0.0168 0.3822 1.0000
5.000 0.7046 0.01158 0.00422 -0.0161 0.3634 1.0000
5.250 0.7286 0.01184 0.00447 -0.0155 0.3437 1.0000
5.500 0.7522 0.01214 0.00474 -0.0148 0.3221 1.0000
5.750 0.7755 0.01247 0.00507 -0.0140 0.2983 1.0000
6.000 0.7983 0.01286 0.00540 -0.0133 0.2724 1.0000
6.250 0.8206 0.01329 0.00578 -0.0125 0.2467 1.0000
6.500 0.8424 0.01379 0.00620 -0.0116 0.2179 1.0000
6.750 0.8634 0.01438 0.00668 -0.0107 0.1858 1.0000
7.000 0.8836 0.01504 0.00723 -0.0097 0.1550 1.0000
7.250 0.9031 0.01578 0.00782 -0.0087 0.1238 1.0000
7.500 0.9224 0.01651 0.00845 -0.0077 0.0976 1.0000
7.750 0.9420 0.01720 0.00909 -0.0066 0.0785 1.0000
8.000 0.9607 0.01797 0.00981 -0.0054 0.0615 1.0000
8.250 0.9788 0.01879 0.01061 -0.0042 0.0454 1.0000
8.500 0.9954 0.01975 0.01156 -0.0028 0.0330 1.0000
8.750 1.0118 0.02069 0.01254 -0.0013 0.0260 1.0000
9.000 1.0271 0.02171 0.01361 0.0002 0.0224 1.0000
9.250 1.0430 0.02261 0.01463 0.0017 0.0204 1.0000
9.500 1.0571 0.02362 0.01575 0.0033 0.0190 1.0000
9.750 1.0689 0.02476 0.01700 0.0051 0.0180 1.0000
10.000 1.0765 0.02616 0.01851 0.0072 0.0173 1.0000
10.250 1.0854 0.02737 0.01986 0.0092 0.0168 1.0000
10.500 1.0903 0.02863 0.02126 0.0118 0.0164 1.0000
10.750 1.0935 0.03003 0.02278 0.0142 0.0161 1.0000
11.000 1.0968 0.03157 0.02446 0.0160 0.0157 1.0000
11.250 1.1002 0.03330 0.02631 0.0175 0.0153 1.0000
11.500 1.1040 0.03510 0.02824 0.0185 0.0146 1.0000
11.750 1.1073 0.03704 0.03028 0.0192 0.0140 1.0000
12.000 1.1090 0.03931 0.03267 0.0198 0.0137 1.0000
12.250 1.1105 0.04170 0.03518 0.0201 0.0134 1.0000
12.500 1.1111 0.04430 0.03792 0.0202 0.0132 1.0000
12.750 1.1107 0.04710 0.04084 0.0202 0.0130 1.0000
13.000 1.1080 0.05031 0.04417 0.0200 0.0127 1.0000
13.250 1.1049 0.05368 0.04768 0.0197 0.0125 1.0000
13.500 1.1007 0.05732 0.05147 0.0191 0.0124 1.0000
13.750 1.0968 0.06098 0.05531 0.0182 0.0123 1.0000
14.000 1.0899 0.06522 0.05975 0.0167 0.0122 1.0000
14.250 1.0815 0.06982 0.06455 0.0149 0.0122 1.0000
14.500 1.0725 0.07466 0.06957 0.0127 0.0121 1.0000
14.750 1.0607 0.08022 0.07532 0.0099 0.0120 1.0000
15.000 1.0486 0.08612 0.08140 0.0068 0.0120 1.0000
15.250 1.0348 0.09267 0.08813 0.0032 0.0121 1.0000
15.500 1.0200 0.09972 0.09534 -0.0008 0.0120 1.0000
15.750 1.0041 0.10746 0.10325 -0.0054 0.0120 1.0000
16.000 0.9869 0.11574 0.11168 -0.0102 0.0121 1.0000
16.250 0.9683 0.12484 0.12092 -0.0156 0.0122 1.0000
16.500 0.9473 0.13512 0.13133 -0.0216 0.0122 1.0000
16.750 0.9255 0.14618 0.14250 -0.0279 0.0124 1.0000
|
Polar data table (+)
Polar graphs
<< Back to E221 (9.39%) (e221-il)