RG 14 9.5% AIRFOIL (rg1495-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG 14 9.5% AIRFOIL (rg1495-il) Reynolds number: 500,000 Max Cl/Cd: 82.08 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg1495-il-500000.txt Download as CSV file: xf-rg1495-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: RG 14 9.5% 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5318 0.09195 0.08960 -0.0249 1.0000 0.0240
-10.000 -0.6174 0.06016 0.05786 -0.0457 1.0000 0.0164
-9.750 -0.6459 0.05361 0.05119 -0.0504 1.0000 0.0160
-9.500 -0.6757 0.04956 0.04701 -0.0483 1.0000 0.0159
-9.250 -0.7033 0.04411 0.04133 -0.0459 1.0000 0.0155
-9.000 -0.7223 0.03893 0.03579 -0.0427 1.0000 0.0156
-8.750 -0.7343 0.03414 0.03056 -0.0391 1.0000 0.0156
-8.500 -0.7335 0.03097 0.02700 -0.0361 1.0000 0.0162
-8.250 -0.7274 0.02845 0.02411 -0.0333 1.0000 0.0165
-8.000 -0.7168 0.02668 0.02202 -0.0308 1.0000 0.0168
-7.750 -0.7117 0.02305 0.01793 -0.0279 1.0000 0.0173
-7.500 -0.6987 0.02087 0.01552 -0.0258 1.0000 0.0177
-7.250 -0.6817 0.01988 0.01446 -0.0242 1.0000 0.0185
-7.000 -0.6637 0.01907 0.01356 -0.0227 1.0000 0.0193
-6.750 -0.6452 0.01823 0.01261 -0.0211 1.0000 0.0201
-6.500 -0.6218 0.01769 0.01195 -0.0205 0.9995 0.0214
-6.250 -0.5864 0.01708 0.01117 -0.0222 0.9972 0.0223
-6.000 -0.5558 0.01493 0.00885 -0.0233 0.9951 0.0237
-5.750 -0.5218 0.01423 0.00812 -0.0248 0.9927 0.0253
-5.500 -0.4877 0.01369 0.00753 -0.0263 0.9895 0.0272
-5.250 -0.4525 0.01313 0.00690 -0.0279 0.9867 0.0286
-5.000 -0.4172 0.01234 0.00603 -0.0296 0.9844 0.0302
-4.750 -0.3843 0.01167 0.00535 -0.0309 0.9810 0.0331
-4.500 -0.3508 0.01126 0.00491 -0.0321 0.9767 0.0361
-4.250 -0.3149 0.01075 0.00436 -0.0338 0.9736 0.0402
-4.000 -0.2772 0.01026 0.00390 -0.0359 0.9713 0.0511
-3.750 -0.2465 0.00971 0.00352 -0.0366 0.9658 0.0824
-3.500 -0.2117 0.00927 0.00324 -0.0382 0.9617 0.1204
-3.250 -0.1744 0.00882 0.00298 -0.0404 0.9589 0.1674
-3.000 -0.1398 0.00837 0.00275 -0.0420 0.9550 0.2269
-2.750 -0.1101 0.00787 0.00254 -0.0425 0.9479 0.3030
-2.500 -0.0767 0.00726 0.00232 -0.0439 0.9432 0.4097
-2.250 -0.0508 0.00665 0.00215 -0.0436 0.9334 0.5309
-2.000 -0.0234 0.00608 0.00202 -0.0434 0.9246 0.6538
-1.750 0.0039 0.00577 0.00200 -0.0429 0.9144 0.7449
-1.500 0.0304 0.00568 0.00200 -0.0421 0.9019 0.7956
-1.250 0.0572 0.00565 0.00198 -0.0414 0.8888 0.8261
-1.000 0.0833 0.00565 0.00197 -0.0405 0.8748 0.8496
-0.750 0.1092 0.00567 0.00195 -0.0397 0.8599 0.8683
-0.500 0.1346 0.00570 0.00194 -0.0387 0.8444 0.8832
-0.250 0.1597 0.00574 0.00193 -0.0377 0.8281 0.8960
0.000 0.1842 0.00579 0.00192 -0.0365 0.8099 0.9081
0.250 0.2081 0.00585 0.00192 -0.0352 0.7886 0.9199
0.500 0.2324 0.00592 0.00191 -0.0340 0.7684 0.9308
0.750 0.2571 0.00600 0.00192 -0.0330 0.7490 0.9410
1.000 0.2843 0.00609 0.00194 -0.0325 0.7275 0.9496
1.250 0.3121 0.00620 0.00197 -0.0322 0.7068 0.9588
1.500 0.3448 0.00632 0.00201 -0.0330 0.6837 0.9654
1.750 0.3762 0.00646 0.00204 -0.0336 0.6581 0.9718
2.000 0.4145 0.00663 0.00210 -0.0358 0.6322 0.9756
2.250 0.4516 0.00678 0.00217 -0.0378 0.6067 0.9801
2.500 0.4869 0.00696 0.00223 -0.0394 0.5768 0.9845
2.750 0.5241 0.00715 0.00229 -0.0415 0.5421 0.9878
3.000 0.5589 0.00734 0.00236 -0.0431 0.5091 0.9918
3.250 0.5931 0.00755 0.00244 -0.0446 0.4745 0.9953
3.500 0.6283 0.00777 0.00254 -0.0464 0.4409 0.9987
3.750 0.6542 0.00797 0.00264 -0.0463 0.4112 1.0000
4.000 0.6718 0.00819 0.00275 -0.0444 0.3810 1.0000
4.250 0.6889 0.00844 0.00289 -0.0424 0.3493 1.0000
4.500 0.7059 0.00871 0.00305 -0.0404 0.3178 1.0000
4.750 0.7229 0.00906 0.00324 -0.0384 0.2809 1.0000
5.000 0.7411 0.00945 0.00347 -0.0367 0.2422 1.0000
5.250 0.7601 0.00989 0.00373 -0.0352 0.2038 1.0000
5.500 0.7803 0.01034 0.00403 -0.0339 0.1725 1.0000
5.750 0.8017 0.01077 0.00435 -0.0328 0.1521 1.0000
6.000 0.8243 0.01114 0.00467 -0.0319 0.1363 1.0000
6.250 0.8473 0.01150 0.00499 -0.0311 0.1206 1.0000
6.500 0.8703 0.01188 0.00533 -0.0303 0.1041 1.0000
6.750 0.8931 0.01230 0.00569 -0.0295 0.0906 1.0000
7.000 0.9158 0.01274 0.00610 -0.0287 0.0801 1.0000
7.250 0.9380 0.01323 0.00656 -0.0278 0.0705 1.0000
7.500 0.9604 0.01371 0.00702 -0.0269 0.0618 1.0000
7.750 0.9834 0.01411 0.00746 -0.0262 0.0551 1.0000
8.000 1.0043 0.01473 0.00805 -0.0252 0.0481 1.0000
8.250 1.0276 0.01509 0.00846 -0.0245 0.0434 1.0000
8.500 1.0474 0.01580 0.00915 -0.0233 0.0381 1.0000
8.750 1.0702 0.01620 0.00963 -0.0226 0.0347 1.0000
9.000 1.0888 0.01699 0.01041 -0.0212 0.0303 1.0000
9.250 1.1103 0.01748 0.01098 -0.0203 0.0274 1.0000
9.500 1.1294 0.01818 0.01168 -0.0191 0.0239 1.0000
9.750 1.1471 0.01898 0.01256 -0.0177 0.0213 1.0000
10.000 1.1661 0.01963 0.01326 -0.0165 0.0191 1.0000
10.250 1.1751 0.02109 0.01479 -0.0139 0.0171 1.0000
10.500 1.1927 0.02178 0.01560 -0.0125 0.0162 1.0000
10.750 1.2075 0.02264 0.01655 -0.0107 0.0151 1.0000
11.000 1.2199 0.02347 0.01745 -0.0086 0.0143 1.0000
11.250 1.2283 0.02450 0.01854 -0.0060 0.0136 1.0000
11.500 1.2239 0.02653 0.02069 -0.0020 0.0128 1.0000
11.750 1.2335 0.02753 0.02181 0.0000 0.0125 1.0000
12.000 1.2415 0.02867 0.02308 0.0022 0.0120 1.0000
12.250 1.2483 0.02990 0.02445 0.0041 0.0115 1.0000
12.500 1.2525 0.03140 0.02607 0.0061 0.0111 1.0000
12.750 1.2557 0.03305 0.02782 0.0078 0.0108 1.0000
13.000 1.2563 0.03503 0.02993 0.0093 0.0106 1.0000
13.250 1.2579 0.03696 0.03195 0.0103 0.0102 1.0000
13.500 1.2550 0.03959 0.03471 0.0112 0.0101 1.0000
13.750 1.2507 0.04251 0.03776 0.0117 0.0099 1.0000
14.000 1.2432 0.04601 0.04140 0.0116 0.0097 1.0000
14.250 1.2306 0.05044 0.04601 0.0109 0.0096 1.0000
14.500 1.2167 0.05537 0.05113 0.0096 0.0095 1.0000
14.750 1.2075 0.05994 0.05586 0.0079 0.0095 1.0000
15.000 1.1877 0.06645 0.06258 0.0050 0.0094 1.0000
15.250 1.1732 0.07247 0.06876 0.0019 0.0094 1.0000
15.750 1.1447 0.08567 0.08230 -0.0057 0.0093 1.0000
16.000 1.1255 0.09366 0.09045 -0.0104 0.0094 1.0000
16.250 1.1067 0.10199 0.09893 -0.0155 0.0094 1.0000
16.500 1.0879 0.11084 0.10792 -0.0209 0.0094 1.0000
16.750 1.0752 0.11859 0.11580 -0.0257 0.0094 1.0000
17.000 1.0572 0.12794 0.12528 -0.0314 0.0095 1.0000
17.250 1.0389 0.13780 0.13526 -0.0374 0.0096 1.0000
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