E221 (9.39%) (e221-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: E221 (9.39%) (e221-il) Reynolds number: 100,000 Max Cl/Cd: 48.18 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e221-il-100000-n5.txt Download as CSV file: xf-e221-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5269 0.11077 0.10585 0.0047 1.0000 0.0308
-9.750 -0.5332 0.10354 0.09866 -0.0002 1.0000 0.0254
-9.500 -0.5302 0.09964 0.09480 -0.0013 1.0000 0.0248
-9.250 -0.5285 0.09556 0.09076 -0.0031 1.0000 0.0242
-9.000 -0.5288 0.09106 0.08631 -0.0054 1.0000 0.0236
-8.750 -0.5310 0.08622 0.08153 -0.0082 1.0000 0.0230
-8.500 -0.5347 0.08112 0.07649 -0.0116 1.0000 0.0225
-8.250 -0.5434 0.07506 0.07050 -0.0167 1.0000 0.0219
-8.000 -0.5542 0.06824 0.06366 -0.0213 1.0000 0.0212
-7.750 -0.5729 0.05721 0.05224 -0.0261 1.0000 0.0195
-7.500 -0.5719 0.05288 0.04772 -0.0264 1.0000 0.0194
-7.250 -0.5682 0.04871 0.04327 -0.0262 1.0000 0.0192
-7.000 -0.5620 0.04465 0.03890 -0.0256 1.0000 0.0191
-6.750 -0.5534 0.04076 0.03462 -0.0247 1.0000 0.0190
-6.500 -0.5423 0.03711 0.03054 -0.0234 1.0000 0.0190
-6.250 -0.5286 0.03388 0.02682 -0.0219 1.0000 0.0192
-6.000 -0.5128 0.03107 0.02351 -0.0203 1.0000 0.0197
-5.750 -0.4955 0.02917 0.02147 -0.0193 1.0000 0.0208
-5.500 -0.4767 0.02759 0.01970 -0.0180 1.0000 0.0221
-5.250 -0.4578 0.02578 0.01761 -0.0165 1.0000 0.0231
-5.000 -0.4391 0.02400 0.01552 -0.0148 1.0000 0.0237
-4.750 -0.4205 0.02251 0.01383 -0.0131 0.9994 0.0245
-4.500 -0.3828 0.02086 0.01191 -0.0150 0.9846 0.0259
-4.250 -0.3484 0.01936 0.01038 -0.0166 0.9679 0.0283
-4.000 -0.3131 0.01846 0.00935 -0.0182 0.9507 0.0339
-3.750 -0.2800 0.01733 0.00814 -0.0193 0.9334 0.0418
-3.500 -0.2483 0.01627 0.00712 -0.0200 0.9165 0.0653
-3.250 -0.2194 0.01525 0.00650 -0.0204 0.8996 0.1396
-3.000 -0.1934 0.01440 0.00607 -0.0202 0.8823 0.2412
-2.750 -0.1690 0.01368 0.00573 -0.0195 0.8657 0.3557
-2.500 -0.1462 0.01295 0.00549 -0.0183 0.8499 0.4958
-2.250 -0.1220 0.01225 0.00535 -0.0168 0.8354 0.6575
-2.000 -0.0652 0.01189 0.00535 -0.0207 0.8241 0.8462
-1.750 -0.0082 0.01201 0.00525 -0.0254 0.8114 0.9213
-1.500 0.0325 0.01216 0.00516 -0.0274 0.7972 0.9599
-1.250 0.0803 0.01219 0.00492 -0.0313 0.7832 0.9857
-1.000 0.1249 0.01212 0.00463 -0.0348 0.7689 1.0000
-0.750 0.1478 0.01213 0.00447 -0.0338 0.7545 1.0000
-0.500 0.1709 0.01216 0.00434 -0.0329 0.7405 1.0000
-0.250 0.1942 0.01221 0.00424 -0.0320 0.7269 1.0000
0.000 0.2181 0.01226 0.00417 -0.0312 0.7135 1.0000
0.250 0.2420 0.01233 0.00412 -0.0304 0.7005 1.0000
0.500 0.2660 0.01241 0.00409 -0.0296 0.6876 1.0000
0.750 0.2900 0.01250 0.00408 -0.0288 0.6750 1.0000
1.000 0.3141 0.01259 0.00408 -0.0280 0.6626 1.0000
1.250 0.3382 0.01270 0.00410 -0.0272 0.6503 1.0000
1.500 0.3624 0.01281 0.00414 -0.0264 0.6378 1.0000
1.750 0.3868 0.01293 0.00421 -0.0256 0.6246 1.0000
2.000 0.4112 0.01305 0.00431 -0.0249 0.6116 1.0000
2.250 0.4356 0.01319 0.00440 -0.0242 0.5985 1.0000
2.500 0.4600 0.01333 0.00451 -0.0234 0.5854 1.0000
2.750 0.4843 0.01348 0.00463 -0.0227 0.5720 1.0000
3.000 0.5087 0.01363 0.00479 -0.0219 0.5586 1.0000
3.250 0.5330 0.01380 0.00494 -0.0211 0.5447 1.0000
3.500 0.5573 0.01397 0.00511 -0.0204 0.5305 1.0000
3.750 0.5815 0.01416 0.00529 -0.0196 0.5158 1.0000
4.000 0.6056 0.01435 0.00552 -0.0188 0.5005 1.0000
4.250 0.6297 0.01456 0.00574 -0.0180 0.4848 1.0000
4.500 0.6536 0.01478 0.00598 -0.0172 0.4687 1.0000
4.750 0.6774 0.01502 0.00623 -0.0164 0.4522 1.0000
5.000 0.7009 0.01527 0.00653 -0.0156 0.4351 1.0000
5.250 0.7244 0.01554 0.00685 -0.0147 0.4163 1.0000
5.500 0.7475 0.01584 0.00718 -0.0139 0.3963 1.0000
5.750 0.7702 0.01616 0.00752 -0.0129 0.3759 1.0000
6.000 0.7927 0.01652 0.00795 -0.0120 0.3533 1.0000
6.250 0.8148 0.01691 0.00837 -0.0111 0.3297 1.0000
6.500 0.8362 0.01737 0.00882 -0.0101 0.3045 1.0000
6.750 0.8571 0.01789 0.00933 -0.0090 0.2778 1.0000
7.000 0.8774 0.01848 0.00994 -0.0080 0.2502 1.0000
7.250 0.8970 0.01915 0.01059 -0.0068 0.2223 1.0000
7.500 0.9158 0.01991 0.01133 -0.0057 0.1949 1.0000
7.750 0.9334 0.02079 0.01213 -0.0045 0.1655 1.0000
8.000 0.9497 0.02179 0.01301 -0.0033 0.1315 1.0000
8.250 0.9649 0.02292 0.01399 -0.0020 0.1015 1.0000
8.500 0.9801 0.02403 0.01511 -0.0006 0.0804 1.0000
8.750 0.9928 0.02537 0.01636 0.0009 0.0620 1.0000
9.000 1.0044 0.02679 0.01780 0.0027 0.0488 1.0000
9.250 1.0138 0.02832 0.01937 0.0046 0.0416 1.0000
9.500 1.0220 0.02987 0.02106 0.0066 0.0372 1.0000
9.750 1.0294 0.03140 0.02272 0.0087 0.0343 1.0000
10.000 1.0339 0.03304 0.02444 0.0108 0.0323 1.0000
10.250 1.0338 0.03486 0.02631 0.0134 0.0307 1.0000
10.500 1.0387 0.03647 0.02811 0.0152 0.0291 1.0000
10.750 1.0427 0.03827 0.03010 0.0168 0.0275 1.0000
11.000 1.0463 0.04023 0.03220 0.0179 0.0263 1.0000
11.250 1.0494 0.04238 0.03447 0.0189 0.0254 1.0000
11.500 1.0517 0.04472 0.03693 0.0196 0.0246 1.0000
11.750 1.0540 0.04720 0.03951 0.0202 0.0241 1.0000
12.000 1.0556 0.05000 0.04241 0.0208 0.0235 1.0000
12.250 1.0572 0.05295 0.04552 0.0211 0.0232 1.0000
12.500 1.0562 0.05617 0.04899 0.0211 0.0229 1.0000
12.750 1.0527 0.05978 0.05284 0.0206 0.0227 1.0000
13.000 1.0455 0.06393 0.05725 0.0196 0.0224 1.0000
13.250 1.0359 0.06850 0.06206 0.0180 0.0222 1.0000
13.500 1.0240 0.07358 0.06737 0.0158 0.0221 1.0000
13.750 1.0109 0.07911 0.07310 0.0131 0.0221 1.0000
14.000 0.9936 0.08565 0.07985 0.0095 0.0220 1.0000
14.250 0.9749 0.09285 0.08724 0.0053 0.0221 1.0000
14.500 0.9563 0.10056 0.09511 0.0007 0.0223 1.0000
14.750 0.9344 0.10964 0.10433 -0.0050 0.0225 1.0000
15.000 0.9127 0.11937 0.11417 -0.0108 0.0228 1.0000
15.250 0.8897 0.13022 0.12509 -0.0172 0.0231 1.0000
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Polar data table (+)
Polar graphs
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