EPPLER 521 AIRFOIL (e521-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 521 AIRFOIL (e521-il) Reynolds number: 500,000 Max Cl/Cd: 56.41 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e521-il-500000-n5.txt Download as CSV file: xf-e521-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 521 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -1.0080 0.11060 0.10720 -0.0029 1.0000 0.0032
-17.500 -1.0293 0.10197 0.09843 -0.0077 1.0000 0.0031
-17.250 -1.0516 0.09336 0.08967 -0.0125 1.0000 0.0032
-17.000 -1.0689 0.08596 0.08212 -0.0166 1.0000 0.0032
-16.750 -1.0845 0.07910 0.07512 -0.0204 1.0000 0.0031
-16.500 -1.1004 0.07242 0.06829 -0.0240 1.0000 0.0032
-16.250 -1.1130 0.06660 0.06231 -0.0270 1.0000 0.0031
-16.000 -1.1225 0.06154 0.05711 -0.0294 1.0000 0.0031
-15.750 -1.1287 0.05722 0.05266 -0.0312 1.0000 0.0033
-15.500 -1.1358 0.05302 0.04833 -0.0327 1.0000 0.0034
-15.250 -1.1407 0.04936 0.04454 -0.0338 1.0000 0.0034
-15.000 -1.1451 0.04601 0.04105 -0.0344 1.0000 0.0035
-14.750 -1.1470 0.04314 0.03806 -0.0347 1.0000 0.0034
-14.500 -1.1471 0.04059 0.03538 -0.0346 1.0000 0.0036
-14.250 -1.1452 0.03835 0.03303 -0.0344 1.0000 0.0037
-14.000 -1.1436 0.03618 0.03075 -0.0339 1.0000 0.0038
-13.750 -1.1404 0.03423 0.02869 -0.0333 1.0000 0.0038
-13.500 -1.1388 0.03221 0.02658 -0.0324 1.0000 0.0042
-13.250 -1.1332 0.03060 0.02490 -0.0315 1.0000 0.0045
-13.000 -1.1265 0.02911 0.02333 -0.0305 1.0000 0.0047
-12.750 -1.1179 0.02782 0.02195 -0.0294 1.0000 0.0049
-12.500 -1.1086 0.02660 0.02065 -0.0284 1.0000 0.0052
-12.250 -1.0987 0.02545 0.01942 -0.0272 1.0000 0.0056
-12.000 -1.0886 0.02433 0.01823 -0.0260 1.0000 0.0060
-11.750 -1.0775 0.02331 0.01718 -0.0248 1.0000 0.0068
-11.500 -1.0504 0.02231 0.01603 -0.0267 0.9233 0.0075
-11.250 -1.0375 0.02162 0.01518 -0.0252 0.8959 0.0082
-11.000 -1.0269 0.02089 0.01434 -0.0233 0.8810 0.0092
-10.750 -1.0149 0.02021 0.01358 -0.0215 0.8708 0.0103
-10.500 -1.0014 0.01962 0.01290 -0.0198 0.8633 0.0115
-10.250 -0.9881 0.01902 0.01223 -0.0180 0.8565 0.0127
-10.000 -0.9751 0.01844 0.01161 -0.0160 0.8507 0.0149
-9.750 -0.9600 0.01798 0.01108 -0.0143 0.8454 0.0164
-9.500 -0.9448 0.01744 0.01050 -0.0126 0.8410 0.0191
-9.250 -0.9264 0.01697 0.00998 -0.0114 0.8374 0.0218
-9.000 -0.9072 0.01648 0.00946 -0.0104 0.8337 0.0249
-8.750 -0.8876 0.01600 0.00896 -0.0093 0.8299 0.0288
-8.500 -0.8672 0.01555 0.00849 -0.0084 0.8266 0.0334
-8.250 -0.8464 0.01512 0.00804 -0.0075 0.8239 0.0393
-8.000 -0.8251 0.01465 0.00760 -0.0068 0.8210 0.0470
-7.750 -0.8029 0.01423 0.00717 -0.0061 0.8179 0.0553
-7.500 -0.7802 0.01386 0.00680 -0.0055 0.8149 0.0640
-7.250 -0.7576 0.01346 0.00642 -0.0049 0.8123 0.0751
-7.000 -0.7347 0.01309 0.00607 -0.0043 0.8101 0.0872
-6.750 -0.7110 0.01272 0.00574 -0.0038 0.8075 0.1001
-6.500 -0.6870 0.01237 0.00542 -0.0034 0.8047 0.1146
-6.250 -0.6633 0.01198 0.00511 -0.0030 0.8021 0.1334
-6.000 -0.6393 0.01162 0.00482 -0.0026 0.7996 0.1541
-5.750 -0.6150 0.01130 0.00455 -0.0022 0.7972 0.1742
-5.500 -0.5905 0.01097 0.00429 -0.0018 0.7950 0.1971
-5.250 -0.5655 0.01064 0.00404 -0.0016 0.7925 0.2205
-5.000 -0.5403 0.01033 0.00382 -0.0014 0.7899 0.2450
-4.750 -0.5150 0.01003 0.00361 -0.0012 0.7872 0.2709
-4.500 -0.4896 0.00974 0.00340 -0.0009 0.7847 0.2983
-4.250 -0.4641 0.00946 0.00320 -0.0007 0.7823 0.3261
-4.000 -0.4384 0.00920 0.00302 -0.0005 0.7800 0.3550
-3.750 -0.4125 0.00891 0.00285 -0.0004 0.7770 0.3878
-3.500 -0.3865 0.00863 0.00269 -0.0002 0.7738 0.4197
-3.250 -0.3605 0.00837 0.00253 0.0000 0.7706 0.4523
-3.000 -0.3345 0.00813 0.00239 0.0002 0.7677 0.4859
-2.750 -0.3081 0.00790 0.00227 0.0003 0.7645 0.5191
-2.500 -0.2814 0.00769 0.00218 0.0004 0.7606 0.5517
-2.250 -0.2546 0.00751 0.00211 0.0006 0.7567 0.5838
-2.000 -0.2273 0.00739 0.00206 0.0007 0.7532 0.6109
-1.750 -0.1996 0.00731 0.00204 0.0007 0.7494 0.6332
-1.500 -0.1713 0.00725 0.00203 0.0006 0.7446 0.6512
-1.250 -0.1431 0.00722 0.00202 0.0006 0.7402 0.6659
-1.000 -0.1147 0.00721 0.00200 0.0005 0.7359 0.6781
-0.750 -0.0860 0.00719 0.00202 0.0004 0.7304 0.6885
-0.500 -0.0574 0.00718 0.00200 0.0003 0.7252 0.6975
-0.250 -0.0287 0.00718 0.00200 0.0001 0.7197 0.7060
0.000 0.0000 0.00718 0.00201 0.0000 0.7129 0.7128
0.250 0.0287 0.00718 0.00200 -0.0001 0.7060 0.7197
0.500 0.0574 0.00718 0.00201 -0.0003 0.6975 0.7252
0.750 0.0860 0.00719 0.00202 -0.0004 0.6884 0.7304
1.000 0.1147 0.00721 0.00200 -0.0005 0.6782 0.7360
1.250 0.1431 0.00722 0.00201 -0.0006 0.6658 0.7402
1.500 0.1714 0.00725 0.00203 -0.0007 0.6512 0.7446
1.750 0.1996 0.00731 0.00204 -0.0007 0.6334 0.7494
2.000 0.2274 0.00739 0.00206 -0.0007 0.6108 0.7532
2.250 0.2546 0.00751 0.00211 -0.0006 0.5838 0.7567
2.500 0.2814 0.00769 0.00218 -0.0004 0.5520 0.7606
2.750 0.3081 0.00790 0.00227 -0.0003 0.5192 0.7645
3.000 0.3345 0.00812 0.00239 -0.0002 0.4862 0.7677
3.250 0.3605 0.00837 0.00253 0.0000 0.4524 0.7706
3.500 0.3865 0.00863 0.00269 0.0002 0.4197 0.7738
3.750 0.4125 0.00891 0.00285 0.0004 0.3876 0.7769
4.000 0.4383 0.00920 0.00302 0.0005 0.3543 0.7800
4.250 0.4641 0.00946 0.00320 0.0007 0.3261 0.7823
4.500 0.4896 0.00973 0.00340 0.0009 0.2986 0.7847
4.750 0.5149 0.01003 0.00361 0.0012 0.2709 0.7872
5.000 0.5402 0.01034 0.00382 0.0014 0.2448 0.7899
5.250 0.5654 0.01064 0.00404 0.0016 0.2205 0.7925
5.500 0.5904 0.01097 0.00429 0.0019 0.1972 0.7950
5.750 0.6148 0.01130 0.00455 0.0022 0.1742 0.7972
6.000 0.6392 0.01162 0.00482 0.0026 0.1540 0.7996
6.250 0.6631 0.01199 0.00511 0.0030 0.1332 0.8021
6.500 0.6869 0.01237 0.00542 0.0035 0.1147 0.8047
6.750 0.7108 0.01272 0.00574 0.0039 0.1001 0.8075
7.000 0.7345 0.01309 0.00607 0.0043 0.0871 0.8101
7.250 0.7574 0.01346 0.00642 0.0049 0.0750 0.8124
7.750 0.8027 0.01423 0.00717 0.0061 0.0554 0.8179
8.000 0.8248 0.01465 0.00759 0.0068 0.0470 0.8210
8.250 0.8461 0.01512 0.00804 0.0076 0.0394 0.8240
8.500 0.8669 0.01555 0.00848 0.0085 0.0334 0.8267
8.750 0.8872 0.01599 0.00896 0.0094 0.0288 0.8300
9.000 0.9068 0.01648 0.00945 0.0104 0.0249 0.8337
9.250 0.9260 0.01696 0.00997 0.0115 0.0217 0.8375
9.500 0.9444 0.01744 0.01050 0.0127 0.0191 0.8411
9.750 0.9596 0.01797 0.01107 0.0144 0.0164 0.8455
10.000 0.9747 0.01843 0.01160 0.0161 0.0149 0.8509
10.250 0.9881 0.01899 0.01222 0.0180 0.0132 0.8566
10.500 1.0008 0.01963 0.01291 0.0199 0.0117 0.8635
10.750 1.0145 0.02020 0.01358 0.0216 0.0104 0.8711
11.000 1.0265 0.02088 0.01433 0.0234 0.0092 0.8813
11.500 1.0500 0.02232 0.01605 0.0267 0.0077 0.9248
11.750 1.0772 0.02330 0.01717 0.0249 0.0067 1.0000
12.000 1.0885 0.02432 0.01823 0.0261 0.0061 1.0000
12.250 1.0985 0.02545 0.01942 0.0273 0.0056 1.0000
12.500 1.1087 0.02657 0.02062 0.0284 0.0054 1.0000
12.750 1.1183 0.02776 0.02189 0.0294 0.0048 1.0000
13.000 1.1265 0.02909 0.02330 0.0305 0.0047 1.0000
13.250 1.1333 0.03056 0.02484 0.0315 0.0043 1.0000
13.500 1.1390 0.03217 0.02653 0.0324 0.0041 1.0000
13.750 1.1412 0.03413 0.02859 0.0333 0.0039 1.0000
14.000 1.1435 0.03615 0.03072 0.0340 0.0038 1.0000
14.250 1.1463 0.03821 0.03288 0.0344 0.0037 1.0000
14.500 1.1472 0.04055 0.03534 0.0347 0.0036 1.0000
14.750 1.1474 0.04307 0.03799 0.0347 0.0035 1.0000
15.000 1.1459 0.04591 0.04095 0.0344 0.0034 1.0000
15.250 1.1408 0.04933 0.04451 0.0338 0.0033 1.0000
15.500 1.1378 0.05274 0.04803 0.0328 0.0034 1.0000
15.750 1.1324 0.05668 0.05211 0.0314 0.0033 1.0000
16.000 1.1237 0.06134 0.05690 0.0294 0.0032 1.0000
16.250 1.1125 0.06668 0.06239 0.0269 0.0033 1.0000
16.500 1.1018 0.07220 0.06805 0.0240 0.0033 1.0000
16.750 1.0875 0.07857 0.07458 0.0206 0.0031 1.0000
17.000 1.0709 0.08563 0.08178 0.0168 0.0032 1.0000
17.250 1.0523 0.09327 0.08958 0.0125 0.0032 1.0000
17.500 1.0323 0.10141 0.09786 0.0080 0.0032 1.0000
17.750 1.0091 0.11042 0.10702 0.0029 0.0032 1.0000
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