R140 12.04% (smoothed) (r140sm-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: R140 12.04% (smoothed) (r140sm-il) Reynolds number: 50,000 Max Cl/Cd: 29.37 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-r140sm-il-50000-n5.txt Download as CSV file: xf-r140sm-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: R140 12.04% (smoothed)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5691 0.09886 0.09191 -0.0336 1.0000 0.0372
-10.750 -0.5782 0.09265 0.08574 -0.0372 1.0000 0.0367
-10.500 -0.5906 0.08686 0.07996 -0.0406 1.0000 0.0362
-10.250 -0.6064 0.08150 0.07459 -0.0434 1.0000 0.0357
-10.000 -0.6243 0.07682 0.06986 -0.0450 1.0000 0.0353
-9.750 -0.6430 0.07282 0.06578 -0.0451 1.0000 0.0351
-9.500 -0.6614 0.06941 0.06228 -0.0437 1.0000 0.0348
-9.250 -0.6789 0.06637 0.05912 -0.0410 1.0000 0.0346
-9.000 -0.6914 0.06323 0.05581 -0.0383 1.0000 0.0344
-8.750 -0.7009 0.06005 0.05241 -0.0355 1.0000 0.0342
-8.500 -0.7071 0.05693 0.04904 -0.0325 1.0000 0.0341
-8.250 -0.7104 0.05381 0.04562 -0.0294 1.0000 0.0341
-8.000 -0.7108 0.05077 0.04225 -0.0262 1.0000 0.0343
-7.750 -0.7078 0.04791 0.03904 -0.0231 1.0000 0.0349
-7.500 -0.7019 0.04531 0.03605 -0.0202 1.0000 0.0364
-7.250 -0.6935 0.04285 0.03301 -0.0172 1.0000 0.0386
-7.000 -0.6813 0.04065 0.03028 -0.0144 1.0000 0.0402
-6.750 -0.6629 0.03764 0.02709 -0.0131 1.0000 0.0417
-6.500 -0.6408 0.03525 0.02453 -0.0120 1.0000 0.0436
-6.250 -0.6147 0.03319 0.02227 -0.0112 1.0000 0.0463
-6.000 -0.5884 0.03155 0.02035 -0.0102 1.0000 0.0515
-5.750 -0.5704 0.03011 0.01893 -0.0085 1.0000 0.0589
-5.500 -0.5543 0.02891 0.01750 -0.0061 1.0000 0.0653
-5.250 -0.5457 0.02758 0.01619 -0.0030 1.0000 0.0722
-5.000 -0.5386 0.02640 0.01500 0.0004 1.0000 0.0845
-4.750 -0.5332 0.02512 0.01380 0.0038 1.0000 0.1099
-4.500 -0.5308 0.02338 0.01254 0.0074 1.0000 0.1706
-4.250 -0.5428 0.02081 0.01203 0.0135 1.0000 0.4619
-4.000 -0.5432 0.02072 0.01250 0.0203 1.0000 0.6309
-3.750 -0.5321 0.02112 0.01301 0.0255 1.0000 0.7056
-3.500 -0.5141 0.02223 0.01413 0.0306 1.0000 0.7730
-3.250 -0.4878 0.02319 0.01486 0.0334 1.0000 0.8146
-3.000 -0.4447 0.02339 0.01466 0.0303 0.9926 0.8311
-2.750 -0.3990 0.02345 0.01428 0.0262 0.9846 0.8418
-2.500 -0.3562 0.02344 0.01395 0.0225 0.9756 0.8526
-2.250 -0.3142 0.02344 0.01367 0.0190 0.9666 0.8637
-2.000 -0.2650 0.02351 0.01343 0.0142 0.9596 0.8727
-1.750 -0.2206 0.02352 0.01324 0.0103 0.9507 0.8819
-1.500 -0.1756 0.02352 0.01305 0.0061 0.9428 0.8918
-1.250 -0.1266 0.02354 0.01288 0.0013 0.9351 0.8998
-1.000 -0.0789 0.02353 0.01274 -0.0034 0.9274 0.9080
-0.750 -0.0320 0.02349 0.01260 -0.0079 0.9198 0.9170
-0.500 0.0170 0.02345 0.01248 -0.0128 0.9119 0.9242
-0.250 0.0645 0.02337 0.01236 -0.0174 0.9049 0.9329
0.000 0.1089 0.02331 0.01228 -0.0215 0.8957 0.9413
0.250 0.1555 0.02320 0.01220 -0.0260 0.8881 0.9494
0.500 0.1970 0.02314 0.01217 -0.0295 0.8791 0.9592
0.750 0.2420 0.02303 0.01212 -0.0337 0.8702 0.9672
1.000 0.2878 0.02289 0.01209 -0.0380 0.8629 0.9754
1.250 0.3277 0.02284 0.01215 -0.0413 0.8529 0.9850
1.500 0.3713 0.02273 0.01217 -0.0453 0.8442 0.9935
1.750 0.4124 0.02260 0.01223 -0.0488 0.8361 1.0000
2.000 0.4291 0.02275 0.01248 -0.0476 0.8246 1.0000
2.250 0.4466 0.02292 0.01276 -0.0464 0.8139 1.0000
2.500 0.4671 0.02306 0.01304 -0.0457 0.8045 1.0000
2.750 0.4878 0.02322 0.01334 -0.0449 0.7951 1.0000
3.000 0.5031 0.02353 0.01387 -0.0432 0.7845 1.0000
3.250 0.5207 0.02381 0.01433 -0.0418 0.7747 1.0000
3.500 0.5445 0.02397 0.01470 -0.0412 0.7665 1.0000
3.750 0.5591 0.02433 0.01527 -0.0392 0.7550 1.0000
4.000 0.5773 0.02453 0.01571 -0.0373 0.7422 1.0000
4.250 0.6023 0.02429 0.01572 -0.0357 0.7256 1.0000
4.500 0.6245 0.02367 0.01541 -0.0326 0.6977 1.0000
4.750 0.6384 0.02275 0.01460 -0.0273 0.6503 1.0000
5.000 0.6380 0.02172 0.01321 -0.0187 0.5452 1.0000
5.250 0.6299 0.02236 0.01255 -0.0109 0.3042 1.0000
5.500 0.6155 0.02507 0.01386 -0.0051 0.1296 1.0000
5.750 0.6128 0.02706 0.01544 -0.0007 0.0899 1.0000
6.000 0.6154 0.02857 0.01686 0.0031 0.0714 1.0000
6.250 0.6209 0.02985 0.01816 0.0064 0.0600 1.0000
6.500 0.6267 0.03123 0.01956 0.0098 0.0547 1.0000
6.750 0.6387 0.03253 0.02105 0.0125 0.0507 1.0000
7.000 0.6589 0.03406 0.02271 0.0142 0.0466 1.0000
7.250 0.6914 0.03609 0.02489 0.0141 0.0425 1.0000
7.500 0.7204 0.03792 0.02707 0.0145 0.0377 1.0000
7.750 0.7473 0.04029 0.02970 0.0150 0.0352 1.0000
8.000 0.7691 0.04296 0.03265 0.0160 0.0341 1.0000
8.250 0.7856 0.04582 0.03581 0.0175 0.0334 1.0000
8.500 0.7972 0.04887 0.03917 0.0194 0.0329 1.0000
8.750 0.8044 0.05201 0.04264 0.0217 0.0326 1.0000
9.000 0.8074 0.05531 0.04625 0.0243 0.0324 1.0000
9.250 0.8069 0.05860 0.04982 0.0268 0.0321 1.0000
9.500 0.8032 0.06178 0.05327 0.0295 0.0320 1.0000
9.750 0.7947 0.06497 0.05665 0.0323 0.0318 1.0000
10.000 0.7801 0.06762 0.05955 0.0356 0.0316 1.0000
10.250 0.7696 0.07077 0.06283 0.0379 0.0318 1.0000
10.500 0.7499 0.07383 0.06609 0.0399 0.0316 1.0000
10.750 0.7326 0.07736 0.06976 0.0406 0.0316 1.0000
11.000 0.7193 0.08140 0.07390 0.0403 0.0318 1.0000
11.250 0.7032 0.08589 0.07848 0.0392 0.0319 1.0000
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Polar data table (+)
Polar graphs
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